TY  - JOUR
AU  - Lukić, Nebojša
AU  - Ivanov, Toni
AU  - Svorcan, Jelena
AU  - Simonović, Aleksandar
PY  - 2024
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7771
AB  - A novel concept of morphing airfoils, capable of changing camber and thickness, is proposed. A variable airfoil shape, defined by six input parameters, is achieved by allowing the three spinal points (at fixed axial positions) to slide vertically, while the upper and lower surfaces are determined by the lengths of the three corresponding ribs that are perpendicular to the spine. Thus, it is possible to find the most appropriate geometric configuration for a wide range of possible operating conditions often present with contemporary unmanned aerial vehicles. Shape optimizations for different Reynolds numbers and different cost functions are performed by coupling a genetic algorithm with simple panel method flow calculations. The obtained airfoils are presented and compared, whereas the proposed concept is validated by more advanced flow simulations. It appears that improvements in aerodynamic performance of nearly 20% can be expected at Re ranging from 0.05 × 106 to 0.1 × 106. The proposed methodology shows promise and can be applied to different types of lifting surfaces, including wing, tail or propeller blade segments. To check the viability of this method for producing airfoils that can be used in a practical sense, structural analysis of one of the obtained geometries using a simplified 1D finite element method as well as a more detailed 3D analysis are performed. The model is then 3D-printed on a fused deposition modeling (FDM) printer with a polyethylene terephthalate glycol (PETG) filament, and the capability of the airfoil to adequately morph between the two desired geometries is experimentally shown.
PB  - MDPI
T2  - Aerospace
T1  - Numerical Investigation and Optimization of a Morphing Airfoil Designed for Lower Reynolds Number
IS  - 4
SP  - 252
VL  - 11
DO  - 10.3390/aerospace11040252
ER  - 

@article{
author = "Lukić, Nebojša and Ivanov, Toni and Svorcan, Jelena and Simonović, Aleksandar",
year = "2024",
abstract = "A novel concept of morphing airfoils, capable of changing camber and thickness, is proposed. A variable airfoil shape, defined by six input parameters, is achieved by allowing the three spinal points (at fixed axial positions) to slide vertically, while the upper and lower surfaces are determined by the lengths of the three corresponding ribs that are perpendicular to the spine. Thus, it is possible to find the most appropriate geometric configuration for a wide range of possible operating conditions often present with contemporary unmanned aerial vehicles. Shape optimizations for different Reynolds numbers and different cost functions are performed by coupling a genetic algorithm with simple panel method flow calculations. The obtained airfoils are presented and compared, whereas the proposed concept is validated by more advanced flow simulations. It appears that improvements in aerodynamic performance of nearly 20% can be expected at Re ranging from 0.05 × 106 to 0.1 × 106. The proposed methodology shows promise and can be applied to different types of lifting surfaces, including wing, tail or propeller blade segments. To check the viability of this method for producing airfoils that can be used in a practical sense, structural analysis of one of the obtained geometries using a simplified 1D finite element method as well as a more detailed 3D analysis are performed. The model is then 3D-printed on a fused deposition modeling (FDM) printer with a polyethylene terephthalate glycol (PETG) filament, and the capability of the airfoil to adequately morph between the two desired geometries is experimentally shown.",
publisher = "MDPI",
journal = "Aerospace",
title = "Numerical Investigation and Optimization of a Morphing Airfoil Designed for Lower Reynolds Number",
number = "4",
pages = "252",
volume = "11",
doi = "10.3390/aerospace11040252"
}

Lukić, N., Ivanov, T., Svorcan, J.,& Simonović, A.. (2024). Numerical Investigation and Optimization of a Morphing Airfoil Designed for Lower Reynolds Number. in Aerospace
MDPI., 11(4), 252.
https://doi.org/10.3390/aerospace11040252

Lukić N, Ivanov T, Svorcan J, Simonović A. Numerical Investigation and Optimization of a Morphing Airfoil Designed for Lower Reynolds Number. in Aerospace. 2024;11(4):252.
doi:10.3390/aerospace11040252 .

Lukić, Nebojša, Ivanov, Toni, Svorcan, Jelena, Simonović, Aleksandar, "Numerical Investigation and Optimization of a Morphing Airfoil Designed for Lower Reynolds Number" in Aerospace, 11, no. 4 (2024):252,
https://doi.org/10.3390/aerospace11040252 . .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Ivanov, Toni
AU  - Simonović, Aleksandar
PY  - 2023
UR  - http://www.ssm.kg.ac.rs/congress_2023/papers/
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/6979
AB  - Modern trends in the development of urban air vehicles and small-scale unmanned air vehicles require them to be as efficient as possible. One option is to improve their aerodynamic performance by semi-active boundary layer control (BLC) techniques, that are more economic and accessible through 3D printing, such as injection/blowing. Flow control generally serves to reduce BL thickness and friction drag, as well as to delay transition and separation. This computational study investigates and quantifies the change in lift and drag coefficients of NACA 23012 airfoil at the critical angle-of-attack (AoA) at M = 0.18 and Re = 1.8 million. Flow simulations are performed using the finite volume method in ANSYS Fluent. Clean and controlled flows are considered steady, incompressible, and viscous. Equations governing the flow are closed by k-ω SST turbulence model. The adopted numerical set-up is validated by available experimental data. Main observations on the possible improvements of aerodynamic performance at a higher angle-of-attack are presented and discussed.
PB  - Српско друштво за механику
C3  - 9th International Congress of the Serbian Society of Mechanics (ICSSM)
T1  - Improving airfoil performance by designed blowing
SP  - 91
UR  - https://hdl.handle.net/21.15107/rcub_machinery_6979
ER  - 

@conference{
author = "Svorcan, Jelena and Ivanov, Toni and Simonović, Aleksandar",
year = "2023",
abstract = "Modern trends in the development of urban air vehicles and small-scale unmanned air vehicles require them to be as efficient as possible. One option is to improve their aerodynamic performance by semi-active boundary layer control (BLC) techniques, that are more economic and accessible through 3D printing, such as injection/blowing. Flow control generally serves to reduce BL thickness and friction drag, as well as to delay transition and separation. This computational study investigates and quantifies the change in lift and drag coefficients of NACA 23012 airfoil at the critical angle-of-attack (AoA) at M = 0.18 and Re = 1.8 million. Flow simulations are performed using the finite volume method in ANSYS Fluent. Clean and controlled flows are considered steady, incompressible, and viscous. Equations governing the flow are closed by k-ω SST turbulence model. The adopted numerical set-up is validated by available experimental data. Main observations on the possible improvements of aerodynamic performance at a higher angle-of-attack are presented and discussed.",
publisher = "Српско друштво за механику",
journal = "9th International Congress of the Serbian Society of Mechanics (ICSSM)",
title = "Improving airfoil performance by designed blowing",
pages = "91",
url = "https://hdl.handle.net/21.15107/rcub_machinery_6979"
}

Svorcan, J., Ivanov, T.,& Simonović, A.. (2023). Improving airfoil performance by designed blowing. in 9th International Congress of the Serbian Society of Mechanics (ICSSM)
Српско друштво за механику., 91.
https://hdl.handle.net/21.15107/rcub_machinery_6979

Svorcan J, Ivanov T, Simonović A. Improving airfoil performance by designed blowing. in 9th International Congress of the Serbian Society of Mechanics (ICSSM). 2023;:91.
https://hdl.handle.net/21.15107/rcub_machinery_6979 .

Svorcan, Jelena, Ivanov, Toni, Simonović, Aleksandar, "Improving airfoil performance by designed blowing" in 9th International Congress of the Serbian Society of Mechanics (ICSSM) (2023):91,
https://hdl.handle.net/21.15107/rcub_machinery_6979 .

TY  - CONF
AU  - Svorcan, Jelena
PY  - 2023
UR  - http://www.ssm.kg.ac.rs/congress_2023/papers/
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/6980
AB  - This talk focuses on flows induced by small-scale propeller blades and the wakes shedding from their tips. Flows around propellers for unmanned air vehicles (approximately 25-75 cm in diameter) in hover are simulated by different approaches to considering turbulence. The challenges to simulating these kinds of flows mainly arise from the relatively low values of Reynolds numbers (several tens to several hundreds of thousands) when transition and other flow phenomena may be expected. The adopted numerical set-ups are validated though comparisons with available experimental data. It can be concluded that global aerodynamic performance can be determined with satisfactory accuracy (the discrepancies between computed and measured values of thrust and torque remain below several percents). However, discerning the actual flow characteristics remains challenging. Here, some distinguishing features of small Re rotational flows are accentuated and discussed. Vortex wakes shedding from the blades are visualized and analyzed. These two benchmark examples provide useful guidelines for further numerical and experimental studies of small-scale propellers.
PB  - Српско друштво за механику
C3  - 9th International Congress of the Serbian Society of Mechanics (ICSSM)
T1  - Numerical investigation of flows around small-scale propellers: Possibilities and challenges
SP  - 145
UR  - https://hdl.handle.net/21.15107/rcub_machinery_6980
ER  - 

@conference{
author = "Svorcan, Jelena",
year = "2023",
abstract = "This talk focuses on flows induced by small-scale propeller blades and the wakes shedding from their tips. Flows around propellers for unmanned air vehicles (approximately 25-75 cm in diameter) in hover are simulated by different approaches to considering turbulence. The challenges to simulating these kinds of flows mainly arise from the relatively low values of Reynolds numbers (several tens to several hundreds of thousands) when transition and other flow phenomena may be expected. The adopted numerical set-ups are validated though comparisons with available experimental data. It can be concluded that global aerodynamic performance can be determined with satisfactory accuracy (the discrepancies between computed and measured values of thrust and torque remain below several percents). However, discerning the actual flow characteristics remains challenging. Here, some distinguishing features of small Re rotational flows are accentuated and discussed. Vortex wakes shedding from the blades are visualized and analyzed. These two benchmark examples provide useful guidelines for further numerical and experimental studies of small-scale propellers.",
publisher = "Српско друштво за механику",
journal = "9th International Congress of the Serbian Society of Mechanics (ICSSM)",
title = "Numerical investigation of flows around small-scale propellers: Possibilities and challenges",
pages = "145",
url = "https://hdl.handle.net/21.15107/rcub_machinery_6980"
}

Svorcan, J.. (2023). Numerical investigation of flows around small-scale propellers: Possibilities and challenges. in 9th International Congress of the Serbian Society of Mechanics (ICSSM)
Српско друштво за механику., 145.
https://hdl.handle.net/21.15107/rcub_machinery_6980

Svorcan J. Numerical investigation of flows around small-scale propellers: Possibilities and challenges. in 9th International Congress of the Serbian Society of Mechanics (ICSSM). 2023;:145.
https://hdl.handle.net/21.15107/rcub_machinery_6980 .

Svorcan, Jelena, "Numerical investigation of flows around small-scale propellers: Possibilities and challenges" in 9th International Congress of the Serbian Society of Mechanics (ICSSM) (2023):145,
https://hdl.handle.net/21.15107/rcub_machinery_6980 .

TY  - CONF
AU  - Peković, Ognjen
AU  - Aleksić, Ivan
AU  - Svorcan, Jelena
AU  - Volf, Goran
AU  - Matić, Dušan
AU  - Kirin, Snežana
AU  - Mitrović, Nenad
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7701
AB  - The pantograph’s purpose is to transfer electrical power from the overhead contact line to the train’s electric propulsion unit. To perform its function adequately, it is necessary to maintain the static contact force between the pantograph and the contact line within the values prescribed by appropriate standards for the entire extension range of the pantograph. The requirement to reach high contact lines complicates the kinematic scheme because the deviation of the trajectory of the pantograph’s collector head from vertical is also prescribed by standards. Further, the structural design of the pantograph is challenging because the greater slenderness ratio of the structure makes it difficult to meet the requirements in terms of stiffness and resistance to vibrations. While at low speeds aerodynamic forces are usually neglected, in high-speed pantographs, they have a significant impact and it is necessary to compensate for them. An aggravating circumstance is the
requirement that the pantograph should work in both knuckle-downstream and knuckle-upstream directions. This paper aims to present the development of a high-speed high–reach pantograph that is developed through the cooperation of company Minel General Electric and the University of Belgrade – Faculty of Mechanical Engineering as well as to present innovative designs of 
 gravitational and aerodynamical compensations that enabled the satisfaction of requested requirements in terms of geometric and static performance.
PB  - University of Belgrade - Faculty of Mechanical Engineering
C3  - International Conference of Experimental and Numerical Investigations and New Technologies CNN TECH 2023
T1  - DEVELOPMENT OF HIGH-REACH PANTOGRAPHS FOR HIGH-SPEED RAILWAYS
SP  - 97
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7701
ER  - 

@conference{
author = "Peković, Ognjen and Aleksić, Ivan and Svorcan, Jelena and Volf, Goran and Matić, Dušan and Kirin, Snežana and Mitrović, Nenad",
year = "2023",
abstract = "The pantograph’s purpose is to transfer electrical power from the overhead contact line to the train’s electric propulsion unit. To perform its function adequately, it is necessary to maintain the static contact force between the pantograph and the contact line within the values prescribed by appropriate standards for the entire extension range of the pantograph. The requirement to reach high contact lines complicates the kinematic scheme because the deviation of the trajectory of the pantograph’s collector head from vertical is also prescribed by standards. Further, the structural design of the pantograph is challenging because the greater slenderness ratio of the structure makes it difficult to meet the requirements in terms of stiffness and resistance to vibrations. While at low speeds aerodynamic forces are usually neglected, in high-speed pantographs, they have a significant impact and it is necessary to compensate for them. An aggravating circumstance is the
requirement that the pantograph should work in both knuckle-downstream and knuckle-upstream directions. This paper aims to present the development of a high-speed high–reach pantograph that is developed through the cooperation of company Minel General Electric and the University of Belgrade – Faculty of Mechanical Engineering as well as to present innovative designs of 
 gravitational and aerodynamical compensations that enabled the satisfaction of requested requirements in terms of geometric and static performance.",
publisher = "University of Belgrade - Faculty of Mechanical Engineering",
journal = "International Conference of Experimental and Numerical Investigations and New Technologies CNN TECH 2023",
title = "DEVELOPMENT OF HIGH-REACH PANTOGRAPHS FOR HIGH-SPEED RAILWAYS",
pages = "97",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7701"
}

Peković, O., Aleksić, I., Svorcan, J., Volf, G., Matić, D., Kirin, S.,& Mitrović, N.. (2023). DEVELOPMENT OF HIGH-REACH PANTOGRAPHS FOR HIGH-SPEED RAILWAYS. in International Conference of Experimental and Numerical Investigations and New Technologies CNN TECH 2023
University of Belgrade - Faculty of Mechanical Engineering., 97.
https://hdl.handle.net/21.15107/rcub_machinery_7701

Peković O, Aleksić I, Svorcan J, Volf G, Matić D, Kirin S, Mitrović N. DEVELOPMENT OF HIGH-REACH PANTOGRAPHS FOR HIGH-SPEED RAILWAYS. in International Conference of Experimental and Numerical Investigations and New Technologies CNN TECH 2023. 2023;:97.
https://hdl.handle.net/21.15107/rcub_machinery_7701 .

Peković, Ognjen, Aleksić, Ivan, Svorcan, Jelena, Volf, Goran, Matić, Dušan, Kirin, Snežana, Mitrović, Nenad, "DEVELOPMENT OF HIGH-REACH PANTOGRAPHS FOR HIGH-SPEED RAILWAYS" in International Conference of Experimental and Numerical Investigations and New Technologies CNN TECH 2023 (2023):97,
https://hdl.handle.net/21.15107/rcub_machinery_7701 .

TY  - JOUR
AU  - Svorcan, Jelena
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7712
AB  - Wall-modeled large-eddy simulation (WMLES) is an advanced mathematical model for turbulent flows which solves for the low-pass filtered numerical solution. A subgrid-scale (SGS) model is used to account for the effects of unresolved small-scale turbulent structures on the resolved scales (i.e. for the dissipation of the smaller scales), while the flow behavior near the walls is modeled by wall functions (thus reducing the requirements for mesh fineness/quality). This paper investigates the possibilities of applying WMLES in the estimation of aerodynamic performance of small-scale propellers, as well as in the analysis of the wake forming downstream. Induced flows around two propellers designed for unmanned air vehicles (approximately 25 cm and 75 cm in diameter) in hover are considered unsteady and turbulent (incompressible or compressible, respectively). Difficulties in computing such flows mainly originate from the relatively low values of Reynolds numbers (several tens to several hundreds of thousands) when transition and other flow phenomena may be present. The choice of the employed numerical model is substantiated by comparisons of resulting numerical with available experimental data. Whereas global quantities, such as thrust and power (coefficients), can be predicted with satisfactory accuracy (up-to several percents), distinguishing the predominant flow features remains challenging (and requires additional computational effort). Here, wakes forming aft of the propeller rotors are visualized and analyzed. These two benchmark examples provide useful guidelines for further numerical and experimental studies of small-scale propellers.
PB  - Srpsko društvo za mehaniku
T2  - Theoretical and Applied Mechanics
T1  - WMLES of flows around small-scale propellers - estimating aerodynamic performance and wake visualization
EP  - 144
IS  - 2
SP  - 133
VL  - 50
DO  - 10.2298/TAM231012010S
ER  - 

@article{
author = "Svorcan, Jelena",
year = "2023",
abstract = "Wall-modeled large-eddy simulation (WMLES) is an advanced mathematical model for turbulent flows which solves for the low-pass filtered numerical solution. A subgrid-scale (SGS) model is used to account for the effects of unresolved small-scale turbulent structures on the resolved scales (i.e. for the dissipation of the smaller scales), while the flow behavior near the walls is modeled by wall functions (thus reducing the requirements for mesh fineness/quality). This paper investigates the possibilities of applying WMLES in the estimation of aerodynamic performance of small-scale propellers, as well as in the analysis of the wake forming downstream. Induced flows around two propellers designed for unmanned air vehicles (approximately 25 cm and 75 cm in diameter) in hover are considered unsteady and turbulent (incompressible or compressible, respectively). Difficulties in computing such flows mainly originate from the relatively low values of Reynolds numbers (several tens to several hundreds of thousands) when transition and other flow phenomena may be present. The choice of the employed numerical model is substantiated by comparisons of resulting numerical with available experimental data. Whereas global quantities, such as thrust and power (coefficients), can be predicted with satisfactory accuracy (up-to several percents), distinguishing the predominant flow features remains challenging (and requires additional computational effort). Here, wakes forming aft of the propeller rotors are visualized and analyzed. These two benchmark examples provide useful guidelines for further numerical and experimental studies of small-scale propellers.",
publisher = "Srpsko društvo za mehaniku",
journal = "Theoretical and Applied Mechanics",
title = "WMLES of flows around small-scale propellers - estimating aerodynamic performance and wake visualization",
pages = "144-133",
number = "2",
volume = "50",
doi = "10.2298/TAM231012010S"
}

Svorcan, J.. (2023). WMLES of flows around small-scale propellers - estimating aerodynamic performance and wake visualization. in Theoretical and Applied Mechanics
Srpsko društvo za mehaniku., 50(2), 133-144.
https://doi.org/10.2298/TAM231012010S

Svorcan J. WMLES of flows around small-scale propellers - estimating aerodynamic performance and wake visualization. in Theoretical and Applied Mechanics. 2023;50(2):133-144.
doi:10.2298/TAM231012010S .

Svorcan, Jelena, "WMLES of flows around small-scale propellers - estimating aerodynamic performance and wake visualization" in Theoretical and Applied Mechanics, 50, no. 2 (2023):133-144,
https://doi.org/10.2298/TAM231012010S . .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Ivey, Christopher
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7002
AB  - Propellers/rotors are usually indispensable parts of unmanned air vehicles that enable them to hover, fly, and maneuver. It is therefore extremely important to understand and resolve various flow structures that are present during flight. Here, the flow around a hovering, small-scale, custom-made propeller is numerically investigated by wall-modeled large eddy simulation (WMLES). Different operating regimes, achieved by changing RPMs, were both measured and computed, and the two sets of results are compared. Additional flow visualizations in the form of instantaneous flow fields are presented. While the computed thrust and power curves follow the expected trends, slight discrepancy between the experimental and numerical values is observed. It can be attributed to differences in the two setups (i.e., some simplifications of the real geometry in the numerical experiment) as well as the complexity of flow transition processes (present at such small Reynolds number flows).
PB  - Springer, Cham.
C3  - New Technologies and Developments in Unmanned Systems. ISUDEF 2022. Sustainable Aviation.
T1  - WMLES of a Small-Scale Hovering Propeller
EP  - 264
SP  - 259
DO  - 10.1007/978-3-031-37160-8_39
ER  - 

@conference{
author = "Svorcan, Jelena and Ivey, Christopher",
year = "2023",
abstract = "Propellers/rotors are usually indispensable parts of unmanned air vehicles that enable them to hover, fly, and maneuver. It is therefore extremely important to understand and resolve various flow structures that are present during flight. Here, the flow around a hovering, small-scale, custom-made propeller is numerically investigated by wall-modeled large eddy simulation (WMLES). Different operating regimes, achieved by changing RPMs, were both measured and computed, and the two sets of results are compared. Additional flow visualizations in the form of instantaneous flow fields are presented. While the computed thrust and power curves follow the expected trends, slight discrepancy between the experimental and numerical values is observed. It can be attributed to differences in the two setups (i.e., some simplifications of the real geometry in the numerical experiment) as well as the complexity of flow transition processes (present at such small Reynolds number flows).",
publisher = "Springer, Cham.",
journal = "New Technologies and Developments in Unmanned Systems. ISUDEF 2022. Sustainable Aviation.",
title = "WMLES of a Small-Scale Hovering Propeller",
pages = "264-259",
doi = "10.1007/978-3-031-37160-8_39"
}

Svorcan, J.,& Ivey, C.. (2023). WMLES of a Small-Scale Hovering Propeller. in New Technologies and Developments in Unmanned Systems. ISUDEF 2022. Sustainable Aviation.
Springer, Cham.., 259-264.
https://doi.org/10.1007/978-3-031-37160-8_39

Svorcan J, Ivey C. WMLES of a Small-Scale Hovering Propeller. in New Technologies and Developments in Unmanned Systems. ISUDEF 2022. Sustainable Aviation.. 2023;:259-264.
doi:10.1007/978-3-031-37160-8_39 .

Svorcan, Jelena, Ivey, Christopher, "WMLES of a Small-Scale Hovering Propeller" in New Technologies and Developments in Unmanned Systems. ISUDEF 2022. Sustainable Aviation. (2023):259-264,
https://doi.org/10.1007/978-3-031-37160-8_39 . .

TY  - JOUR
AU  - Milić, Milica
AU  - Svorcan, Jelena
AU  - Zorić, Nemanja
AU  - Atanasovska, Ivana
AU  - Momčilović, Dejan B.
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/6955
AB  - Composite materials have been extensively employed in the aviation industry in recent years. The application of new materials enables significant weight savings with improved mechanical characteristics. This is also very important in the field of development of unmanned aerial vehicles (UAV). In the design phases, it is necessary to perceive all the aspects that are important for the structure and consider different load cases. The relationship between weight and strength proved to be important. This means that detailed strength analyses of each structural part are indispensable. In particular, primary load-bearing structures must sustain all types of loads without fail. Failure of the structure can affect the motion of the UAV during the mission or lead to a crash and significant losses. This paper presents the research performed on the failure analysis of a composite beam of a novel UAV. During the testing phase, under an unpredictable load condition followed by a crash landing, failure of the structure occurred on a beam element. The study was performed to determine the cause of the failure of certain layers of the composite laminate, because the previous calculation showed that it met the criteria for which it was dimensioned. Based on the telemetry data and the impact load that was registered, a complementary numerical and experimental analyses were performed to determine what happened and why. Composite test specimens were extracted from the beam and subjected to standard tensile tests, in order to determine the actual mechanical characteristics of the layered material. The paper presents in detail the comparison of the results as well as the methodology used in this research.
PB  - London : Sage Publications Ltd
T2  - Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science
T1  - Mathematical modeling and experimental investigation of a composite beam failure - Case study
EP  - 12
SP  - 1
DO  - 10.1177/09544062231179078
ER  - 

@article{
author = "Milić, Milica and Svorcan, Jelena and Zorić, Nemanja and Atanasovska, Ivana and Momčilović, Dejan B.",
year = "2023",
abstract = "Composite materials have been extensively employed in the aviation industry in recent years. The application of new materials enables significant weight savings with improved mechanical characteristics. This is also very important in the field of development of unmanned aerial vehicles (UAV). In the design phases, it is necessary to perceive all the aspects that are important for the structure and consider different load cases. The relationship between weight and strength proved to be important. This means that detailed strength analyses of each structural part are indispensable. In particular, primary load-bearing structures must sustain all types of loads without fail. Failure of the structure can affect the motion of the UAV during the mission or lead to a crash and significant losses. This paper presents the research performed on the failure analysis of a composite beam of a novel UAV. During the testing phase, under an unpredictable load condition followed by a crash landing, failure of the structure occurred on a beam element. The study was performed to determine the cause of the failure of certain layers of the composite laminate, because the previous calculation showed that it met the criteria for which it was dimensioned. Based on the telemetry data and the impact load that was registered, a complementary numerical and experimental analyses were performed to determine what happened and why. Composite test specimens were extracted from the beam and subjected to standard tensile tests, in order to determine the actual mechanical characteristics of the layered material. The paper presents in detail the comparison of the results as well as the methodology used in this research.",
publisher = "London : Sage Publications Ltd",
journal = "Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science",
title = "Mathematical modeling and experimental investigation of a composite beam failure - Case study",
pages = "12-1",
doi = "10.1177/09544062231179078"
}

Milić, M., Svorcan, J., Zorić, N., Atanasovska, I.,& Momčilović, D. B.. (2023). Mathematical modeling and experimental investigation of a composite beam failure - Case study. in Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science
London : Sage Publications Ltd., 1-12.
https://doi.org/10.1177/09544062231179078

Milić M, Svorcan J, Zorić N, Atanasovska I, Momčilović DB. Mathematical modeling and experimental investigation of a composite beam failure - Case study. in Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science. 2023;:1-12.
doi:10.1177/09544062231179078 .

Milić, Milica, Svorcan, Jelena, Zorić, Nemanja, Atanasovska, Ivana, Momčilović, Dejan B., "Mathematical modeling and experimental investigation of a composite beam failure - Case study" in Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science (2023):1-12,
https://doi.org/10.1177/09544062231179078 . .

TY  - CONF
AU  - Stratton, Zachary
AU  - Spyropoulos, John
AU  - Bose, Sanjeeb
AU  - Svorcan, Jelena
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4194
AB  - A scaled helicopter rotor in hover is studied using wall-modeled large-eddy simulations (WMLES). Performance is evaluated for three thrust conditions at varying grid resolutions and validated with experimental measurements. Capturing the effects of the laminar-turbulent transition over the blade, and the subsequent impact on blade forces, poses a significant challenge for the equilibrium wall model. Results indicate that a mesh with around two grid points in the turbulent boundary layer predicts forces that indicate fully turbulent flow over the blade. Meshes with around seven grid points in the turbulent boundary layer can capture some transitional impact on blade forces, despite not accurately predicting transition location. Further confirmation of viscous force impact on rotor loads was evaluated with simulations using a blowing-suction trip to force transition and a wall-model sensor to act as a crude transition model.
C3  - AIAA SCITECH 2023 Forum
T1  - Rotor Performance and Turbulent Wake Simulations of a Scaled Helicopter Rotor in Hover Using Wall-Modeled Large-Eddy Simulations
DO  - 10.2514/6.2023-2636
ER  - 

@conference{
author = "Stratton, Zachary and Spyropoulos, John and Bose, Sanjeeb and Svorcan, Jelena",
year = "2023",
abstract = "A scaled helicopter rotor in hover is studied using wall-modeled large-eddy simulations (WMLES). Performance is evaluated for three thrust conditions at varying grid resolutions and validated with experimental measurements. Capturing the effects of the laminar-turbulent transition over the blade, and the subsequent impact on blade forces, poses a significant challenge for the equilibrium wall model. Results indicate that a mesh with around two grid points in the turbulent boundary layer predicts forces that indicate fully turbulent flow over the blade. Meshes with around seven grid points in the turbulent boundary layer can capture some transitional impact on blade forces, despite not accurately predicting transition location. Further confirmation of viscous force impact on rotor loads was evaluated with simulations using a blowing-suction trip to force transition and a wall-model sensor to act as a crude transition model.",
journal = "AIAA SCITECH 2023 Forum",
title = "Rotor Performance and Turbulent Wake Simulations of a Scaled Helicopter Rotor in Hover Using Wall-Modeled Large-Eddy Simulations",
doi = "10.2514/6.2023-2636"
}

Stratton, Z., Spyropoulos, J., Bose, S.,& Svorcan, J.. (2023). Rotor Performance and Turbulent Wake Simulations of a Scaled Helicopter Rotor in Hover Using Wall-Modeled Large-Eddy Simulations. in AIAA SCITECH 2023 Forum.
https://doi.org/10.2514/6.2023-2636

Stratton Z, Spyropoulos J, Bose S, Svorcan J. Rotor Performance and Turbulent Wake Simulations of a Scaled Helicopter Rotor in Hover Using Wall-Modeled Large-Eddy Simulations. in AIAA SCITECH 2023 Forum. 2023;.
doi:10.2514/6.2023-2636 .

Stratton, Zachary, Spyropoulos, John, Bose, Sanjeeb, Svorcan, Jelena, "Rotor Performance and Turbulent Wake Simulations of a Scaled Helicopter Rotor in Hover Using Wall-Modeled Large-Eddy Simulations" in AIAA SCITECH 2023 Forum (2023),
https://doi.org/10.2514/6.2023-2636 . .

TY  - CONF
AU  - Milić, Milica
AU  - Svorcan, Jelena
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7251
PB  - Springer, Cham.
C3  - Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022
T1  - Preliminary Full Configuration Drag Estimation of Fixed-Wing UAV Using Analytical Aerodynamics
EP  - 310
SP  - 305
DO  - 10.1007/978-3-031-42041-2_37
ER  - 

@conference{
author = "Milić, Milica and Svorcan, Jelena",
year = "2023",
publisher = "Springer, Cham.",
journal = "Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022",
title = "Preliminary Full Configuration Drag Estimation of Fixed-Wing UAV Using Analytical Aerodynamics",
pages = "310-305",
doi = "10.1007/978-3-031-42041-2_37"
}

Milić, M.,& Svorcan, J.. (2023). Preliminary Full Configuration Drag Estimation of Fixed-Wing UAV Using Analytical Aerodynamics. in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022
Springer, Cham.., 305-310.
https://doi.org/10.1007/978-3-031-42041-2_37

Milić M, Svorcan J. Preliminary Full Configuration Drag Estimation of Fixed-Wing UAV Using Analytical Aerodynamics. in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022. 2023;:305-310.
doi:10.1007/978-3-031-42041-2_37 .

Milić, Milica, Svorcan, Jelena, "Preliminary Full Configuration Drag Estimation of Fixed-Wing UAV Using Analytical Aerodynamics" in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022 (2023):305-310,
https://doi.org/10.1007/978-3-031-42041-2_37 . .

Karakoc, H., Kostić, I., Grbović, A., Svorcan, J., Dalkiran, A., Ercan, A. H.,& Peković, O.. (2023). Novel Techniques in Maintenance, Repair, and Overhaul. in Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022
Springer, Cham...
https://doi.org/10.1007/978-3-031-42041-2

Karakoc H, Kostić I, Grbović A, Svorcan J, Dalkiran A, Ercan AH, Peković O. Novel Techniques in Maintenance, Repair, and Overhaul. in Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022. 2023;.
doi:10.1007/978-3-031-42041-2 .

Karakoc, Hikmet, Kostić, Ivan, Grbović, Aleksandar, Svorcan, Jelena, Dalkiran, Alper, Ercan, Ali Haydar, Peković, Ognjen, "Novel Techniques in Maintenance, Repair, and Overhaul" in Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022 (2023),
https://doi.org/10.1007/978-3-031-42041-2 . .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Bornhoft, Brett
AU  - Goc, Konrad
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7250
PB  - Springer, Cham.
C3  - Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022
T1  - Comparative Analysis of Flow Fields Around NACA 23012 Airfoil at Three Characteristic Angles-of-Attack
EP  - 175
SP  - 169
DO  - 10.1007/978-3-031-42041-2_22
ER  - 

@conference{
author = "Svorcan, Jelena and Bornhoft, Brett and Goc, Konrad",
year = "2023",
publisher = "Springer, Cham.",
journal = "Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022",
title = "Comparative Analysis of Flow Fields Around NACA 23012 Airfoil at Three Characteristic Angles-of-Attack",
pages = "175-169",
doi = "10.1007/978-3-031-42041-2_22"
}

Svorcan, J., Bornhoft, B.,& Goc, K.. (2023). Comparative Analysis of Flow Fields Around NACA 23012 Airfoil at Three Characteristic Angles-of-Attack. in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022
Springer, Cham.., 169-175.
https://doi.org/10.1007/978-3-031-42041-2_22

Svorcan J, Bornhoft B, Goc K. Comparative Analysis of Flow Fields Around NACA 23012 Airfoil at Three Characteristic Angles-of-Attack. in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022. 2023;:169-175.
doi:10.1007/978-3-031-42041-2_22 .

Svorcan, Jelena, Bornhoft, Brett, Goc, Konrad, "Comparative Analysis of Flow Fields Around NACA 23012 Airfoil at Three Characteristic Angles-of-Attack" in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022 (2023):169-175,
https://doi.org/10.1007/978-3-031-42041-2_22 . .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Wang, Kan
AU  - Kovačević, Aleksandar
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7248
PB  - Springer, Cham.
C3  - Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022
T1  - Accounting for the Effects of Experimental Setting in Propeller Flow Computation
EP  - 66
SP  - 61
DO  - 10.1007/978-3-031-42041-2_9
ER  - 

@conference{
author = "Svorcan, Jelena and Wang, Kan and Kovačević, Aleksandar",
year = "2023",
publisher = "Springer, Cham.",
journal = "Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022",
title = "Accounting for the Effects of Experimental Setting in Propeller Flow Computation",
pages = "66-61",
doi = "10.1007/978-3-031-42041-2_9"
}

Svorcan, J., Wang, K.,& Kovačević, A.. (2023). Accounting for the Effects of Experimental Setting in Propeller Flow Computation. in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022
Springer, Cham.., 61-66.
https://doi.org/10.1007/978-3-031-42041-2_9

Svorcan J, Wang K, Kovačević A. Accounting for the Effects of Experimental Setting in Propeller Flow Computation. in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022. 2023;:61-66.
doi:10.1007/978-3-031-42041-2_9 .

Svorcan, Jelena, Wang, Kan, Kovačević, Aleksandar, "Accounting for the Effects of Experimental Setting in Propeller Flow Computation" in Novel Techniques in Maintenance, Repair, and Overhaul Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2022 (2023):61-66,
https://doi.org/10.1007/978-3-031-42041-2_9 . .

TY  - GEN
AU  - Smiljanić, Milče
AU  - Vorkapić, Miloš
AU  - Cvetanović, Katarina
AU  - Milinković, Evgenija
AU  - Lazić, Žarko
AU  - Bošković, Marko V.
AU  - Svorcan, Jelena
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7072
T1  - Metoda za posmatranje i analizu protoka fluida u Si-Pyrex staklo opto-mikrofluidnim platformama
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7072
ER  - 

@misc{
author = "Smiljanić, Milče and Vorkapić, Miloš and Cvetanović, Katarina and Milinković, Evgenija and Lazić, Žarko and Bošković, Marko V. and Svorcan, Jelena",
year = "2023",
title = "Metoda za posmatranje i analizu protoka fluida u Si-Pyrex staklo opto-mikrofluidnim platformama",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7072"
}

Smiljanić, M., Vorkapić, M., Cvetanović, K., Milinković, E., Lazić, Ž., Bošković, M. V.,& Svorcan, J.. (2023). Metoda za posmatranje i analizu protoka fluida u Si-Pyrex staklo opto-mikrofluidnim platformama. .
https://hdl.handle.net/21.15107/rcub_machinery_7072

Smiljanić M, Vorkapić M, Cvetanović K, Milinković E, Lazić Ž, Bošković MV, Svorcan J. Metoda za posmatranje i analizu protoka fluida u Si-Pyrex staklo opto-mikrofluidnim platformama. 2023;.
https://hdl.handle.net/21.15107/rcub_machinery_7072 .

Smiljanić, Milče, Vorkapić, Miloš, Cvetanović, Katarina, Milinković, Evgenija, Lazić, Žarko, Bošković, Marko V., Svorcan, Jelena, "Metoda za posmatranje i analizu protoka fluida u Si-Pyrex staklo opto-mikrofluidnim platformama" (2023),
https://hdl.handle.net/21.15107/rcub_machinery_7072 .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Kovačević, Aleksandar
AU  - Popović, Lazar
AU  - Simonović, Aleksandar
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7073
PB  - Springer
PB  - SARES
C3  - Solutions for Maintenance Repair and Overhaul, Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2021
T1  - Sizing and Performance Analysis of a Single-Seat Tandem Helicopter
EP  - 227
SP  - 219
DO  - 10.1007/978-3-031-38446-2
ER  - 

@conference{
author = "Svorcan, Jelena and Kovačević, Aleksandar and Popović, Lazar and Simonović, Aleksandar",
year = "2023",
publisher = "Springer, SARES",
journal = "Solutions for Maintenance Repair and Overhaul, Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2021",
title = "Sizing and Performance Analysis of a Single-Seat Tandem Helicopter",
pages = "227-219",
doi = "10.1007/978-3-031-38446-2"
}

Svorcan, J., Kovačević, A., Popović, L.,& Simonović, A.. (2023). Sizing and Performance Analysis of a Single-Seat Tandem Helicopter. in Solutions for Maintenance Repair and Overhaul, Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2021
Springer., 219-227.
https://doi.org/10.1007/978-3-031-38446-2

Svorcan J, Kovačević A, Popović L, Simonović A. Sizing and Performance Analysis of a Single-Seat Tandem Helicopter. in Solutions for Maintenance Repair and Overhaul, Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2021. 2023;:219-227.
doi:10.1007/978-3-031-38446-2 .

Svorcan, Jelena, Kovačević, Aleksandar, Popović, Lazar, Simonović, Aleksandar, "Sizing and Performance Analysis of a Single-Seat Tandem Helicopter" in Solutions for Maintenance Repair and Overhaul, Proceedings of the International Symposium on Aviation Technology, MRO, and Operations 2021 (2023):219-227,
https://doi.org/10.1007/978-3-031-38446-2 . .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Čantrak, Đorđe
AU  - Andrić, Jelena
AU  - Ianiro, Andrea
PY  - 2023
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7057
AB  - The idea of urban air mobility is steadily gaining popularity for its enormous potential to radically
change the way modern cities are functioning and are being planned. In its present form, it relies
on numerous vertical take-off and landing (VTOL) unmanned air vehicles (UAVs) of different sizes
that will perform a number of tasks: deliveries, transport, surveillance and control, etc. On the
other hand, to progress further, urban air mobility will also require abundant infrastructure on the
ground (heliports, charging stations, communication hubs, etc.) as well as large amounts of energy
that should be generated primarily from renewable resources. There are still many technological
challenges to solve, such as efficient aircraft design, quiet rotors, electrical propulsion and storage,
autonomous flight, optimized routes, etc. This paper describes an initial study of possible operation
of several different UAVs (from the smallest to medium size) including the estimation of their
required power and expected performance (such as useful weight, range and endurance) and
proposes some options for future urban air mobility over Belgrade.
PB  - Union of Mechanical and Electrotechnical Engineers and Technicians of Serbia (SMEITS) Society for Renewable Electrical Power Sources
C3  - 11th International Conference on Renewable Electrical Power Sources
T1  - Prospects of Urban Air Mobility in Belgrade, Serbia
EP  - 251
SP  - 245
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7057
ER  - 

@conference{
author = "Svorcan, Jelena and Čantrak, Đorđe and Andrić, Jelena and Ianiro, Andrea",
year = "2023",
abstract = "The idea of urban air mobility is steadily gaining popularity for its enormous potential to radically
change the way modern cities are functioning and are being planned. In its present form, it relies
on numerous vertical take-off and landing (VTOL) unmanned air vehicles (UAVs) of different sizes
that will perform a number of tasks: deliveries, transport, surveillance and control, etc. On the
other hand, to progress further, urban air mobility will also require abundant infrastructure on the
ground (heliports, charging stations, communication hubs, etc.) as well as large amounts of energy
that should be generated primarily from renewable resources. There are still many technological
challenges to solve, such as efficient aircraft design, quiet rotors, electrical propulsion and storage,
autonomous flight, optimized routes, etc. This paper describes an initial study of possible operation
of several different UAVs (from the smallest to medium size) including the estimation of their
required power and expected performance (such as useful weight, range and endurance) and
proposes some options for future urban air mobility over Belgrade.",
publisher = "Union of Mechanical and Electrotechnical Engineers and Technicians of Serbia (SMEITS) Society for Renewable Electrical Power Sources",
journal = "11th International Conference on Renewable Electrical Power Sources",
title = "Prospects of Urban Air Mobility in Belgrade, Serbia",
pages = "251-245",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7057"
}

Svorcan, J., Čantrak, Đ., Andrić, J.,& Ianiro, A.. (2023). Prospects of Urban Air Mobility in Belgrade, Serbia. in 11th International Conference on Renewable Electrical Power Sources
Union of Mechanical and Electrotechnical Engineers and Technicians of Serbia (SMEITS) Society for Renewable Electrical Power Sources., 245-251.
https://hdl.handle.net/21.15107/rcub_machinery_7057

Svorcan J, Čantrak Đ, Andrić J, Ianiro A. Prospects of Urban Air Mobility in Belgrade, Serbia. in 11th International Conference on Renewable Electrical Power Sources. 2023;:245-251.
https://hdl.handle.net/21.15107/rcub_machinery_7057 .

Svorcan, Jelena, Čantrak, Đorđe, Andrić, Jelena, Ianiro, Andrea, "Prospects of Urban Air Mobility in Belgrade, Serbia" in 11th International Conference on Renewable Electrical Power Sources (2023):245-251,
https://hdl.handle.net/21.15107/rcub_machinery_7057 .

TY  - CONF
AU  - Tanović, Dragoljub
AU  - Svorcan, Jelena
AU  - Ivanović, Milica
AU  - Baltić, Marija
AU  - Vorkapić, Miloš
AU  - Telebak, Katarina
AU  - Stojanović, Jagoš
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7747
AB  - The wind speed is one of the major parameter influencing the design of the wind turbine, which varies widely over the different part of the country and globe. So, significant research is going on for the design of wind turbine for low, medium and high wind speed. Currently, many researchers have started designing small-scale horizontal axis wind turbines (HAWT) in world, to adapt their use to households. The advantage is reflected in the simple and affordable construction, uninterrupted operation and satisfactory power that wind turbines create. An airfoil is defined as the cross section of a body that is placed in an airstream in order to produce a useful aerodynamic force in the most efficient manner possible. The cross sections of wings, propeller blades, windmill blades, compressor and turbine blades in a jet engine, and hydrofoils are example of airfoils. A computational study has been conducted on various airfoils to simulate flows at different Reynolds numbers (Re) and wind speed to provide understanding and guidance for other low Reynolds-number designs. The numerical computational method used in this study is a boundary element method (BEM) which is implemented in software Qblade. It is an alternative deterministic method which incorporates a mesh that is only located on the boundaries of the domain and hence are attractive for free surface problems. The airfoils investigated in this study include NACA 4412, NACA 63-415 and S809. Performances such as power, power coefficient and tip speed ratio were compared.
PB  - Innovation Center of Faculty of Mechanical Engineering
C3  - International Conference of Experimental and Numerical Investigations and New Technologies
T1  - THE INFLUENCE OF THE REYNOLDS NUMBER ON THE  AIRFOILS
SP  - 63
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7747
ER  - 

@conference{
author = "Tanović, Dragoljub and Svorcan, Jelena and Ivanović, Milica and Baltić, Marija and Vorkapić, Miloš and Telebak, Katarina and Stojanović, Jagoš",
year = "2022",
abstract = "The wind speed is one of the major parameter influencing the design of the wind turbine, which varies widely over the different part of the country and globe. So, significant research is going on for the design of wind turbine for low, medium and high wind speed. Currently, many researchers have started designing small-scale horizontal axis wind turbines (HAWT) in world, to adapt their use to households. The advantage is reflected in the simple and affordable construction, uninterrupted operation and satisfactory power that wind turbines create. An airfoil is defined as the cross section of a body that is placed in an airstream in order to produce a useful aerodynamic force in the most efficient manner possible. The cross sections of wings, propeller blades, windmill blades, compressor and turbine blades in a jet engine, and hydrofoils are example of airfoils. A computational study has been conducted on various airfoils to simulate flows at different Reynolds numbers (Re) and wind speed to provide understanding and guidance for other low Reynolds-number designs. The numerical computational method used in this study is a boundary element method (BEM) which is implemented in software Qblade. It is an alternative deterministic method which incorporates a mesh that is only located on the boundaries of the domain and hence are attractive for free surface problems. The airfoils investigated in this study include NACA 4412, NACA 63-415 and S809. Performances such as power, power coefficient and tip speed ratio were compared.",
publisher = "Innovation Center of Faculty of Mechanical Engineering",
journal = "International Conference of Experimental and Numerical Investigations and New Technologies",
title = "THE INFLUENCE OF THE REYNOLDS NUMBER ON THE  AIRFOILS",
pages = "63",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7747"
}

Tanović, D., Svorcan, J., Ivanović, M., Baltić, M., Vorkapić, M., Telebak, K.,& Stojanović, J.. (2022). THE INFLUENCE OF THE REYNOLDS NUMBER ON THE  AIRFOILS. in International Conference of Experimental and Numerical Investigations and New Technologies
Innovation Center of Faculty of Mechanical Engineering., 63.
https://hdl.handle.net/21.15107/rcub_machinery_7747

Tanović D, Svorcan J, Ivanović M, Baltić M, Vorkapić M, Telebak K, Stojanović J. THE INFLUENCE OF THE REYNOLDS NUMBER ON THE  AIRFOILS. in International Conference of Experimental and Numerical Investigations and New Technologies. 2022;:63.
https://hdl.handle.net/21.15107/rcub_machinery_7747 .

Tanović, Dragoljub, Svorcan, Jelena, Ivanović, Milica, Baltić, Marija, Vorkapić, Miloš, Telebak, Katarina, Stojanović, Jagoš, "THE INFLUENCE OF THE REYNOLDS NUMBER ON THE  AIRFOILS" in International Conference of Experimental and Numerical Investigations and New Technologies (2022):63,
https://hdl.handle.net/21.15107/rcub_machinery_7747 .

TY  - CHAP
AU  - Svorcan, Jelena
AU  - Wang, Kan
AU  - Ivey, Christopher
AU  - Kovačević, Aleksandar
PY  - 2022
UR  - https://ctr.stanford.edu/publications/annual-research-briefs/annual-research-briefs-2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/7597
PB  - Stanford University, Center for Turbulence Research
T2  - Annual Research Briefs 2022, Center for Turbulence Research​, Stanford University
T1  - Estimating the performance of a small-scale non-isolated propeller in hover using WMLES
EP  - 95
SP  - 87
UR  - https://hdl.handle.net/21.15107/rcub_machinery_7597
ER  - 

@inbook{
author = "Svorcan, Jelena and Wang, Kan and Ivey, Christopher and Kovačević, Aleksandar",
year = "2022",
publisher = "Stanford University, Center for Turbulence Research",
journal = "Annual Research Briefs 2022, Center for Turbulence Research​, Stanford University",
booktitle = "Estimating the performance of a small-scale non-isolated propeller in hover using WMLES",
pages = "95-87",
url = "https://hdl.handle.net/21.15107/rcub_machinery_7597"
}

Svorcan, J., Wang, K., Ivey, C.,& Kovačević, A.. (2022). Estimating the performance of a small-scale non-isolated propeller in hover using WMLES. in Annual Research Briefs 2022, Center for Turbulence Research​, Stanford University
Stanford University, Center for Turbulence Research., 87-95.
https://hdl.handle.net/21.15107/rcub_machinery_7597

Svorcan J, Wang K, Ivey C, Kovačević A. Estimating the performance of a small-scale non-isolated propeller in hover using WMLES. in Annual Research Briefs 2022, Center for Turbulence Research​, Stanford University. 2022;:87-95.
https://hdl.handle.net/21.15107/rcub_machinery_7597 .

Svorcan, Jelena, Wang, Kan, Ivey, Christopher, Kovačević, Aleksandar, "Estimating the performance of a small-scale non-isolated propeller in hover using WMLES" in Annual Research Briefs 2022, Center for Turbulence Research​, Stanford University (2022):87-95,
https://hdl.handle.net/21.15107/rcub_machinery_7597 .

TY  - CONF
AU  - Milić, Milica
AU  - Svorcan, Jelena
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4265
AB  - Advancements in using technology of unmanned aerial systems have made UAVs easier to
operate, more affordable, and capable of performing a broader range of tasks.This has led to a
large expansion of UAV applications in society, which has led to a large expansion of their
applications. However, the main challenge is still to determine the precise location where the
UAV would collect the desired data during an autonomous flight. This type of problem often
occurs when the purpose of an unmanned aerial vehicle is to perform tasks that require high
precision in measurements and when the UAV is not in optical sight. High-precision Global
Navigation Satellite System (GNSS) sensors can be used to solve this problem, but this adds
significant cost and operational complexity to the operation of a UAV. Also, these sensors
cannot be used in urban areas, industrial zones or indoors because the signals become
unreliable. By using RTK (real-time kinematic) GPS, sufficient precision is achieved for the
reconstruction of the aircraft trajectory. This network operates on the principle of a base station,
whose location is precisely determined, while the UAV is a moving body, so it is possible
between these two objects to correct or remove errors that either one of them would observe
themselves. The objective of this paper is to produce localization of a moving UAV, and 3D
visualization its trajectory, using a telemetry data as well as error estimation.
PB  - University of Belgrade, Faculty of Mechanical Engineering
C3  - Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
T1  - Unmanned aerial vehicle trajectory visualization and reconstruction using the changes in significant variables over time
SP  - 112
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4265
ER  - 

@conference{
author = "Milić, Milica and Svorcan, Jelena",
year = "2022",
abstract = "Advancements in using technology of unmanned aerial systems have made UAVs easier to
operate, more affordable, and capable of performing a broader range of tasks.This has led to a
large expansion of UAV applications in society, which has led to a large expansion of their
applications. However, the main challenge is still to determine the precise location where the
UAV would collect the desired data during an autonomous flight. This type of problem often
occurs when the purpose of an unmanned aerial vehicle is to perform tasks that require high
precision in measurements and when the UAV is not in optical sight. High-precision Global
Navigation Satellite System (GNSS) sensors can be used to solve this problem, but this adds
significant cost and operational complexity to the operation of a UAV. Also, these sensors
cannot be used in urban areas, industrial zones or indoors because the signals become
unreliable. By using RTK (real-time kinematic) GPS, sufficient precision is achieved for the
reconstruction of the aircraft trajectory. This network operates on the principle of a base station,
whose location is precisely determined, while the UAV is a moving body, so it is possible
between these two objects to correct or remove errors that either one of them would observe
themselves. The objective of this paper is to produce localization of a moving UAV, and 3D
visualization its trajectory, using a telemetry data as well as error estimation.",
publisher = "University of Belgrade, Faculty of Mechanical Engineering",
journal = "Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering",
title = "Unmanned aerial vehicle trajectory visualization and reconstruction using the changes in significant variables over time",
pages = "112",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4265"
}

Milić, M.,& Svorcan, J.. (2022). Unmanned aerial vehicle trajectory visualization and reconstruction using the changes in significant variables over time. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
University of Belgrade, Faculty of Mechanical Engineering., 112.
https://hdl.handle.net/21.15107/rcub_machinery_4265

Milić M, Svorcan J. Unmanned aerial vehicle trajectory visualization and reconstruction using the changes in significant variables over time. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering. 2022;:112.
https://hdl.handle.net/21.15107/rcub_machinery_4265 .

Milić, Milica, Svorcan, Jelena, "Unmanned aerial vehicle trajectory visualization and reconstruction using the changes in significant variables over time" in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering (2022):112,
https://hdl.handle.net/21.15107/rcub_machinery_4265 .

TY  - CONF
AU  - Trivković, Zorana
AU  - Svorcan, Jelena
AU  - Baltić, Marija
AU  - Zorić, Nemanja
AU  - Peković, Ognjen
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3808
AB  - Vertical-axis wind turbines, despite being somewhat uncommon and less efficient renewable energy converters, still offer many advantages to small consumers and possibilities for further improvement. Their rotor is usually made up of fiber-glass composite blades that can be optimized both aerodynamically and/or structurally. Although the aerodynamics of vertical-axis wind turbine rotors is unsteady, complex and challenging to simulate, it is possible to make a sufficiently accurate estimation of variable aerodynamic loads acting on the blade and use them for its structural dimensioning. This research combines a multi-objective constrained optimization procedure by particle swarm and finite element method with experimental analyses with the purpose of defining the best blade, i.e. the blade of minimal mass, least tip deflection under the loading case corresponding to the aerodynamically most demanding operational regime, greatest difference between its natural frequencies and rated rotor angular frequency, lowest manufacturing cost and complexity, etc. Imposed constraints also include acceptable failure criteria along the blade. Design variables refer to ply lay-up scheme, i.e. lamina thicknesses and orientations. Final solution, chosen from the obtained Pareto set, was manufactured and experimentally validated. The consistency of strains, measured in several different cases of bending, and corresponding numerical values was mostly below 8%. The study demonstrates the applicability of the employed multi-objective optimization methodology in wind turbine blade design. It also proposes an affordable and structurally reliable composite lay-up scheme specifically designed for small-scale vertical-axis wind turbines.
PB  - Springer Science and Business Media Deutschland GmbH
C3  - Lecture Notes in Networks and Systems
T1  - Multi-objective optimization and experimental testing of a laminated vertical-axis wind turbine blade
EP  - 65
SP  - 39
VL  - 323
DO  - 10.1007/978-3-030-86009-7_3
ER  - 

@conference{
author = "Trivković, Zorana and Svorcan, Jelena and Baltić, Marija and Zorić, Nemanja and Peković, Ognjen",
year = "2022",
abstract = "Vertical-axis wind turbines, despite being somewhat uncommon and less efficient renewable energy converters, still offer many advantages to small consumers and possibilities for further improvement. Their rotor is usually made up of fiber-glass composite blades that can be optimized both aerodynamically and/or structurally. Although the aerodynamics of vertical-axis wind turbine rotors is unsteady, complex and challenging to simulate, it is possible to make a sufficiently accurate estimation of variable aerodynamic loads acting on the blade and use them for its structural dimensioning. This research combines a multi-objective constrained optimization procedure by particle swarm and finite element method with experimental analyses with the purpose of defining the best blade, i.e. the blade of minimal mass, least tip deflection under the loading case corresponding to the aerodynamically most demanding operational regime, greatest difference between its natural frequencies and rated rotor angular frequency, lowest manufacturing cost and complexity, etc. Imposed constraints also include acceptable failure criteria along the blade. Design variables refer to ply lay-up scheme, i.e. lamina thicknesses and orientations. Final solution, chosen from the obtained Pareto set, was manufactured and experimentally validated. The consistency of strains, measured in several different cases of bending, and corresponding numerical values was mostly below 8%. The study demonstrates the applicability of the employed multi-objective optimization methodology in wind turbine blade design. It also proposes an affordable and structurally reliable composite lay-up scheme specifically designed for small-scale vertical-axis wind turbines.",
publisher = "Springer Science and Business Media Deutschland GmbH",
journal = "Lecture Notes in Networks and Systems",
title = "Multi-objective optimization and experimental testing of a laminated vertical-axis wind turbine blade",
pages = "65-39",
volume = "323",
doi = "10.1007/978-3-030-86009-7_3"
}

Trivković, Z., Svorcan, J., Baltić, M., Zorić, N.,& Peković, O.. (2022). Multi-objective optimization and experimental testing of a laminated vertical-axis wind turbine blade. in Lecture Notes in Networks and Systems
Springer Science and Business Media Deutschland GmbH., 323, 39-65.
https://doi.org/10.1007/978-3-030-86009-7_3

Trivković Z, Svorcan J, Baltić M, Zorić N, Peković O. Multi-objective optimization and experimental testing of a laminated vertical-axis wind turbine blade. in Lecture Notes in Networks and Systems. 2022;323:39-65.
doi:10.1007/978-3-030-86009-7_3 .

Trivković, Zorana, Svorcan, Jelena, Baltić, Marija, Zorić, Nemanja, Peković, Ognjen, "Multi-objective optimization and experimental testing of a laminated vertical-axis wind turbine blade" in Lecture Notes in Networks and Systems, 323 (2022):39-65,
https://doi.org/10.1007/978-3-030-86009-7_3 . .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Smiljanić, Milče
AU  - Vorkapić, Miloš
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4261
AB  - Microfluidic devices are excessively used for various biomedical, chemical, and engineering
applications. The most common microfluidic platforms are obtained from
polydimethylsiloxane (PDMS). Platforms based on etched silicon wafers anodically bonded to
Pyrex glass are more mechanically rigid, have better sealing and there is no gas permeability
compared to those obtained from PDMS [1,2]. The aim of our work is to numerically analyze
fluid flow in anisotropically etched silicon microchannels sealed with Pyrex glass. We present
simulations of fluid flow in Y-bifurcated microchannels fabricated from the etched {100}
silicon in 25 wt% tetramethylammonium hydroxide (TMAH) water solution at the temperature
of 80°C [3]. We have explored two symmetrical Y-bifurcations that are defined with acute
angles of 36.8° and 19° with the sides that are along the <310> and <610> crystallographic
directions in the masking layer [3], respectively. The angles between obtained sidewalls and
{100} silicon of two ingoing microchannels for the first and second Y-bifurcation are 72.5°
and 80.7°, respectively. The sidewalls of outgoing microchannel in both cases are defined with
<100> crystallographic directions and they are orthogonal to the surface of {100} silicon wafer.
The appropriate widths of ingoing and outgoing microchannels are 300 and 400 μm,
respectively. The depth of microchannels is 55 μm. All simulated flows are three-dimensional
(3D), steady and laminar [4], while the investigated fluid is water. Velocities and pressure
values are defined at the inlet and outlet boundaries, respectively. The resulting flows are
illustrated by velocity contours. The obtained conclusions from fluid flow simulations of
presented simple Y-bifurcations provide guidance for future fabrication of complex
microfluidic platforms by a cost-effective process with good control over microchannel
dimensions.
PB  - University of Belgrade, Faculty of Mechanical Engineering
C3  - Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
T1  - Simulating flow in silicon Y-bifurcated microchannels
SP  - 46
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4261
ER  - 

@conference{
author = "Svorcan, Jelena and Smiljanić, Milče and Vorkapić, Miloš",
year = "2022",
abstract = "Microfluidic devices are excessively used for various biomedical, chemical, and engineering
applications. The most common microfluidic platforms are obtained from
polydimethylsiloxane (PDMS). Platforms based on etched silicon wafers anodically bonded to
Pyrex glass are more mechanically rigid, have better sealing and there is no gas permeability
compared to those obtained from PDMS [1,2]. The aim of our work is to numerically analyze
fluid flow in anisotropically etched silicon microchannels sealed with Pyrex glass. We present
simulations of fluid flow in Y-bifurcated microchannels fabricated from the etched {100}
silicon in 25 wt% tetramethylammonium hydroxide (TMAH) water solution at the temperature
of 80°C [3]. We have explored two symmetrical Y-bifurcations that are defined with acute
angles of 36.8° and 19° with the sides that are along the <310> and <610> crystallographic
directions in the masking layer [3], respectively. The angles between obtained sidewalls and
{100} silicon of two ingoing microchannels for the first and second Y-bifurcation are 72.5°
and 80.7°, respectively. The sidewalls of outgoing microchannel in both cases are defined with
<100> crystallographic directions and they are orthogonal to the surface of {100} silicon wafer.
The appropriate widths of ingoing and outgoing microchannels are 300 and 400 μm,
respectively. The depth of microchannels is 55 μm. All simulated flows are three-dimensional
(3D), steady and laminar [4], while the investigated fluid is water. Velocities and pressure
values are defined at the inlet and outlet boundaries, respectively. The resulting flows are
illustrated by velocity contours. The obtained conclusions from fluid flow simulations of
presented simple Y-bifurcations provide guidance for future fabrication of complex
microfluidic platforms by a cost-effective process with good control over microchannel
dimensions.",
publisher = "University of Belgrade, Faculty of Mechanical Engineering",
journal = "Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering",
title = "Simulating flow in silicon Y-bifurcated microchannels",
pages = "46",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4261"
}

Svorcan, J., Smiljanić, M.,& Vorkapić, M.. (2022). Simulating flow in silicon Y-bifurcated microchannels. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
University of Belgrade, Faculty of Mechanical Engineering., 46.
https://hdl.handle.net/21.15107/rcub_machinery_4261

Svorcan J, Smiljanić M, Vorkapić M. Simulating flow in silicon Y-bifurcated microchannels. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering. 2022;:46.
https://hdl.handle.net/21.15107/rcub_machinery_4261 .

Svorcan, Jelena, Smiljanić, Milče, Vorkapić, Miloš, "Simulating flow in silicon Y-bifurcated microchannels" in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering (2022):46,
https://hdl.handle.net/21.15107/rcub_machinery_4261 .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Griffin, Kevin Patrick
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4262
AB  - The flow field around a NACA 4412 airfoil is numerically investigated by means of large
eddy simulation (LES), an advanced mathematical model for turbulent flows which solves for
the low-pass filtered numerical solution. A subgrid-scale model is used to account for the
effects of unresolved small-scale turbulent structures on the resolved scales, while the flow
behavior near walls is modeled by wall functions [1]. Here, the investigated operating
conditions are a chord Reynolds number of 1.5 million and a Mach number of 0.2 at a high
angle-of-attack of 14°, where strong separation at the aft part of the airfoil suction side can be
observed. This validation case is chosen from the experimental dataset described and available
in [2]. The finest computational grid contains approximately 9 million control volumes. Fluid
flow computations are performed by the second-order low-dissipation finite-volume solver
charLES developed by Cascade Technologies, Inc. The Dynamic Smagorinsky subgrid-scale
model is employed, while a no-penetration stress-based algebraic equilibrium wall model is
applied along the airfoil walls. Velocity and pressure values are defined at inlet and outlet
boundaries, respectively, while periodic walls are used in the span. The obtained numerical
results are validated through comparison to experimental data. Fig. 1 illustrates the pressure
coefficient distributions. In addition, the instantaneous velocity field visualized in Fig. 2
illustrates that the flow structures resolved by the LES exhibit a wide range of length scales.
PB  - University of Belgrade, Faculty of Mechanical Engineering
C3  - Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
T1  - LES of flow around NACA 4412 airfoil at high angle-of-attack
SP  - 50
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4262
ER  - 

@conference{
author = "Svorcan, Jelena and Griffin, Kevin Patrick",
year = "2022",
abstract = "The flow field around a NACA 4412 airfoil is numerically investigated by means of large
eddy simulation (LES), an advanced mathematical model for turbulent flows which solves for
the low-pass filtered numerical solution. A subgrid-scale model is used to account for the
effects of unresolved small-scale turbulent structures on the resolved scales, while the flow
behavior near walls is modeled by wall functions [1]. Here, the investigated operating
conditions are a chord Reynolds number of 1.5 million and a Mach number of 0.2 at a high
angle-of-attack of 14°, where strong separation at the aft part of the airfoil suction side can be
observed. This validation case is chosen from the experimental dataset described and available
in [2]. The finest computational grid contains approximately 9 million control volumes. Fluid
flow computations are performed by the second-order low-dissipation finite-volume solver
charLES developed by Cascade Technologies, Inc. The Dynamic Smagorinsky subgrid-scale
model is employed, while a no-penetration stress-based algebraic equilibrium wall model is
applied along the airfoil walls. Velocity and pressure values are defined at inlet and outlet
boundaries, respectively, while periodic walls are used in the span. The obtained numerical
results are validated through comparison to experimental data. Fig. 1 illustrates the pressure
coefficient distributions. In addition, the instantaneous velocity field visualized in Fig. 2
illustrates that the flow structures resolved by the LES exhibit a wide range of length scales.",
publisher = "University of Belgrade, Faculty of Mechanical Engineering",
journal = "Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering",
title = "LES of flow around NACA 4412 airfoil at high angle-of-attack",
pages = "50",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4262"
}

Svorcan, J.,& Griffin, K. P.. (2022). LES of flow around NACA 4412 airfoil at high angle-of-attack. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
University of Belgrade, Faculty of Mechanical Engineering., 50.
https://hdl.handle.net/21.15107/rcub_machinery_4262

Svorcan J, Griffin KP. LES of flow around NACA 4412 airfoil at high angle-of-attack. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering. 2022;:50.
https://hdl.handle.net/21.15107/rcub_machinery_4262 .

Svorcan, Jelena, Griffin, Kevin Patrick, "LES of flow around NACA 4412 airfoil at high angle-of-attack" in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering (2022):50,
https://hdl.handle.net/21.15107/rcub_machinery_4262 .

TY  - CONF
AU  - Hasan, Mohammad Sakib
AU  - Svorcan, Jelena
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4263
AB  - The design of high-altitude unmanned aerial vehicles is one of the most current research
topics today in the field of aviation. The possible purposes of such flying platforms are
numerous, from communication hubs, terrain observations, performing various measurements
in the upper layers of the atmosphere, to various military uses. However, these are complex
systems that involve many unresolved scientific and research challenges such as: the necessity
of extremely low airframe weight, low air pressure and density cruising at high altitudes where
air pressure and density are much lower than in the Earth’s vicinity, sub-zero temperatures,
exposure to increased radiation, low Re implying accentuated viscosity effects and decreased
aerodynamic characteristics, assuring complete flight autonomy, need to generate the required
energy for flight solely from solar energy, adequate sizing and control of rechargeable batteries,
etc.
At the beginning, the initial mission requirements, mission profile, assessment of daily
power consumption and battery mass as well as methodologies for the initial estimation of
aircraft structural mass and wing loads are discussed. Then a novel high-lift airfoil specially
designed for low-Re high-altitude flight through multi- objective optimization was designed
by using genetic algorithm. Subsequently, aerodynamic analysis of the wing carried out by the
methods of computational fluid mechanics, specifically by solving Navier-Stokes equations
averaged by Reynolds statistics and closed by a 4-equation turbulent model is shown. Finally,
static analyses of the behavior of wing structures under the combined action of calculated
aerodynamic and gravitational loads were performed, as well as dynamic, modal analyses
(important for knowing the response of the structure in non-stationary operating conditions)
using the finite element method.
PB  - University of Belgrade, Faculty of Mechanical Engineering
C3  - Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
T1  - Conceptual design of solar-powered high-altitude long endurance aircraft
SP  - 87
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4263
ER  - 

@conference{
author = "Hasan, Mohammad Sakib and Svorcan, Jelena",
year = "2022",
abstract = "The design of high-altitude unmanned aerial vehicles is one of the most current research
topics today in the field of aviation. The possible purposes of such flying platforms are
numerous, from communication hubs, terrain observations, performing various measurements
in the upper layers of the atmosphere, to various military uses. However, these are complex
systems that involve many unresolved scientific and research challenges such as: the necessity
of extremely low airframe weight, low air pressure and density cruising at high altitudes where
air pressure and density are much lower than in the Earth’s vicinity, sub-zero temperatures,
exposure to increased radiation, low Re implying accentuated viscosity effects and decreased
aerodynamic characteristics, assuring complete flight autonomy, need to generate the required
energy for flight solely from solar energy, adequate sizing and control of rechargeable batteries,
etc.
At the beginning, the initial mission requirements, mission profile, assessment of daily
power consumption and battery mass as well as methodologies for the initial estimation of
aircraft structural mass and wing loads are discussed. Then a novel high-lift airfoil specially
designed for low-Re high-altitude flight through multi- objective optimization was designed
by using genetic algorithm. Subsequently, aerodynamic analysis of the wing carried out by the
methods of computational fluid mechanics, specifically by solving Navier-Stokes equations
averaged by Reynolds statistics and closed by a 4-equation turbulent model is shown. Finally,
static analyses of the behavior of wing structures under the combined action of calculated
aerodynamic and gravitational loads were performed, as well as dynamic, modal analyses
(important for knowing the response of the structure in non-stationary operating conditions)
using the finite element method.",
publisher = "University of Belgrade, Faculty of Mechanical Engineering",
journal = "Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering",
title = "Conceptual design of solar-powered high-altitude long endurance aircraft",
pages = "87",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4263"
}

Hasan, M. S.,& Svorcan, J.. (2022). Conceptual design of solar-powered high-altitude long endurance aircraft. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
University of Belgrade, Faculty of Mechanical Engineering., 87.
https://hdl.handle.net/21.15107/rcub_machinery_4263

Hasan MS, Svorcan J. Conceptual design of solar-powered high-altitude long endurance aircraft. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering. 2022;:87.
https://hdl.handle.net/21.15107/rcub_machinery_4263 .

Hasan, Mohammad Sakib, Svorcan, Jelena, "Conceptual design of solar-powered high-altitude long endurance aircraft" in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering (2022):87,
https://hdl.handle.net/21.15107/rcub_machinery_4263 .

TY  - CONF
AU  - Svorcan, Jelena
AU  - Tanović, Dragoljub
AU  - Kovačević, Aleksandar
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4217
AB  - The growing climate change issues and the ongoing energy crisis stipulate
further exploitation of renewable energy sources and the development of systems
capable to efficiently generate clean energy. Among the most promising are wind
turbines, that come in different shapes and sizes. Small-scale wind turbines are
economic and particularly suitable for small consumers and rural areas. They are not
too common, and further research into their performance is necessary. This paper
focuses on the design and aerodynamic performance of a small horizontal-axis wind
turbine. Its rotor geometry is described while its basic aerodynamic coefficients, power
and thrust coefficients, are computed by finite volume method in ANSYS Fluent. Flow
is assumed as incompressible and viscous, while Reynolds-averaged Navier-Stokes
(RANS) equations are closed by different turbulence models. Wind turbine
aerodynamic performance is estimated, and different flow visualizations are provided,
particularly focusing on the wind turbine wake.
PB  - University of East Sarajevo, Faculty of Mechanical Engineering
C3  - 6th International Scientific Conference on Mechanical Engineering Technologies and Applications COMETa 2022
T1  - Computational aerodynamic analysis of a small wind turbine
EP  - 725
SP  - 719
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4217
ER  - 

@conference{
author = "Svorcan, Jelena and Tanović, Dragoljub and Kovačević, Aleksandar",
year = "2022",
abstract = "The growing climate change issues and the ongoing energy crisis stipulate
further exploitation of renewable energy sources and the development of systems
capable to efficiently generate clean energy. Among the most promising are wind
turbines, that come in different shapes and sizes. Small-scale wind turbines are
economic and particularly suitable for small consumers and rural areas. They are not
too common, and further research into their performance is necessary. This paper
focuses on the design and aerodynamic performance of a small horizontal-axis wind
turbine. Its rotor geometry is described while its basic aerodynamic coefficients, power
and thrust coefficients, are computed by finite volume method in ANSYS Fluent. Flow
is assumed as incompressible and viscous, while Reynolds-averaged Navier-Stokes
(RANS) equations are closed by different turbulence models. Wind turbine
aerodynamic performance is estimated, and different flow visualizations are provided,
particularly focusing on the wind turbine wake.",
publisher = "University of East Sarajevo, Faculty of Mechanical Engineering",
journal = "6th International Scientific Conference on Mechanical Engineering Technologies and Applications COMETa 2022",
title = "Computational aerodynamic analysis of a small wind turbine",
pages = "725-719",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4217"
}

Svorcan, J., Tanović, D.,& Kovačević, A.. (2022). Computational aerodynamic analysis of a small wind turbine. in 6th International Scientific Conference on Mechanical Engineering Technologies and Applications COMETa 2022
University of East Sarajevo, Faculty of Mechanical Engineering., 719-725.
https://hdl.handle.net/21.15107/rcub_machinery_4217

Svorcan J, Tanović D, Kovačević A. Computational aerodynamic analysis of a small wind turbine. in 6th International Scientific Conference on Mechanical Engineering Technologies and Applications COMETa 2022. 2022;:719-725.
https://hdl.handle.net/21.15107/rcub_machinery_4217 .

Svorcan, Jelena, Tanović, Dragoljub, Kovačević, Aleksandar, "Computational aerodynamic analysis of a small wind turbine" in 6th International Scientific Conference on Mechanical Engineering Technologies and Applications COMETa 2022 (2022):719-725,
https://hdl.handle.net/21.15107/rcub_machinery_4217 .

TY  - CONF
AU  - Kovačević, Aleksandar
AU  - Svorcan, Jelena
AU  - Ivanov, Toni
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4264
AB  - Various algorithms are used to control modern unmanned aerial systems. However, thanks
to the simplicity of application, the most commonly used control algorithm for aircraft but also
for other dynamic systems in various industries is the PID (Proportional, Integral, Derivative)
controller. For the proper response of the system and fast stabilization during the action of
certain disturbances during its operation, it is necessary to precisely adjust the parameters of
the PID controller. This paper presents a mathematical model of a seesaw system for which a
PID control simulation was performed for different asymmetric geometries. Asymmetric
geometry implies different positions of the rotor relative to the axis of system rotation, as well
as when the rotor disks do not lie in the same plane, which simulates the influence of inaccuracy
in the construction of multi-rotor UAVs. The control simulation shows the possibility of
compensating for the mentioned geometric irregularities to ensure the appropriate behavior of
the system. The limit values of this influence are also shown, at which the PID control
algorithm cannot adequately perform the correction and ensure the correct response of the
system. The obtained simulation results would be verified by making an adequate physical
model and obtaining experimental results for the same input parameters, which may be the
subject of future research work.
PB  - University of Belgrade, Faculty of Mechanical Engineering
C3  - Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
T1  - Modeling, simulation and control of propeller driven seesaw system with asymmetric geometry using PID controller
SP  - 111
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4264
ER  - 

@conference{
author = "Kovačević, Aleksandar and Svorcan, Jelena and Ivanov, Toni",
year = "2022",
abstract = "Various algorithms are used to control modern unmanned aerial systems. However, thanks
to the simplicity of application, the most commonly used control algorithm for aircraft but also
for other dynamic systems in various industries is the PID (Proportional, Integral, Derivative)
controller. For the proper response of the system and fast stabilization during the action of
certain disturbances during its operation, it is necessary to precisely adjust the parameters of
the PID controller. This paper presents a mathematical model of a seesaw system for which a
PID control simulation was performed for different asymmetric geometries. Asymmetric
geometry implies different positions of the rotor relative to the axis of system rotation, as well
as when the rotor disks do not lie in the same plane, which simulates the influence of inaccuracy
in the construction of multi-rotor UAVs. The control simulation shows the possibility of
compensating for the mentioned geometric irregularities to ensure the appropriate behavior of
the system. The limit values of this influence are also shown, at which the PID control
algorithm cannot adequately perform the correction and ensure the correct response of the
system. The obtained simulation results would be verified by making an adequate physical
model and obtaining experimental results for the same input parameters, which may be the
subject of future research work.",
publisher = "University of Belgrade, Faculty of Mechanical Engineering",
journal = "Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering",
title = "Modeling, simulation and control of propeller driven seesaw system with asymmetric geometry using PID controller",
pages = "111",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4264"
}

Kovačević, A., Svorcan, J.,& Ivanov, T.. (2022). Modeling, simulation and control of propeller driven seesaw system with asymmetric geometry using PID controller. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering
University of Belgrade, Faculty of Mechanical Engineering., 111.
https://hdl.handle.net/21.15107/rcub_machinery_4264

Kovačević A, Svorcan J, Ivanov T. Modeling, simulation and control of propeller driven seesaw system with asymmetric geometry using PID controller. in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering. 2022;:111.
https://hdl.handle.net/21.15107/rcub_machinery_4264 .

Kovačević, Aleksandar, Svorcan, Jelena, Ivanov, Toni, "Modeling, simulation and control of propeller driven seesaw system with asymmetric geometry using PID controller" in Booklet of Abstracts - 1st International Conference on Mathematical Modelling in Mechanics and Engineering (2022):111,
https://hdl.handle.net/21.15107/rcub_machinery_4264 .

TY  - JOUR
AU  - Svorcan, Jelena
AU  - Andrić, Jelena
AU  - Čantrak, Đorđe
AU  - Ivanov, Toni
PY  - 2022
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4173
T2  - Advances in Mechanical Engineering
T1  - Special Collection on advanced practices in aerospace and energy engineering
EP  - 3
IS  - 10
SP  - 1
VL  - 14
DO  - 10.1177/16878132221125578
ER  - 

@article{
author = "Svorcan, Jelena and Andrić, Jelena and Čantrak, Đorđe and Ivanov, Toni",
year = "2022",
journal = "Advances in Mechanical Engineering",
title = "Special Collection on advanced practices in aerospace and energy engineering",
pages = "3-1",
number = "10",
volume = "14",
doi = "10.1177/16878132221125578"
}

Svorcan, J., Andrić, J., Čantrak, Đ.,& Ivanov, T.. (2022). Special Collection on advanced practices in aerospace and energy engineering. in Advances in Mechanical Engineering, 14(10), 1-3.
https://doi.org/10.1177/16878132221125578

Svorcan J, Andrić J, Čantrak Đ, Ivanov T. Special Collection on advanced practices in aerospace and energy engineering. in Advances in Mechanical Engineering. 2022;14(10):1-3.
doi:10.1177/16878132221125578 .

Svorcan, Jelena, Andrić, Jelena, Čantrak, Đorđe, Ivanov, Toni, "Special Collection on advanced practices in aerospace and energy engineering" in Advances in Mechanical Engineering, 14, no. 10 (2022):1-3,
https://doi.org/10.1177/16878132221125578 . .