Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder
Само за регистроване кориснике
2014
Конференцијски прилог (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
Experimental investigation of supersonic flow at Mach number of 2 around a finned ogive cylinder at angles-of-attack ranging from 0° to 16° has been conducted in T-38 trisonic blow-down wind tunnel of the Serbian Military Technical Institute. A short description of testing process and measuring equipment is given. Results of a comparison of experimental and numerical results, that primarily include aerodynamic coefficients and pressure distribution, are presented and discussed. Numerical simulations were performed in ANSYS FLUENT with three Reynolds Averaged Navier-Stokes turbulence models of different complexity. Both structured and unstructured grids were generated, tested and compared and the influence of their nature and size has been considered. Base flow at zero angle-of-attack has been investigated in more detail and the accuracy and applicability of the used models is discussed. Computed fluid flow is presented in the form of pressure coefficient and Mach number contours and ve...locity vectors.
Кључне речи:
supersonic flow / experiment / CFD / turbulent models / pressure coefficientИзвор:
6th International scientific conference on defensive technologies OTEH 2014, 2014, 55-60Издавач:
- Belgrade : Military Technical Institute - VTI
Финансирање / пројекти:
- Истраживање и развој савремених приступа пројектовања композитних лопатица ротора високих перформанси (RS-MESTD-Technological Development (TD or TR)-35035)
Колекције
Институција/група
Mašinski fakultetTY - CONF AU - Komarov, Dragan AU - Svorcan, Jelena AU - Isaković, Jovan AU - Bengin, Aleksandar AU - Ivanov, Toni PY - 2014 UR - https://machinery.mas.bg.ac.rs/handle/123456789/4455 AB - Experimental investigation of supersonic flow at Mach number of 2 around a finned ogive cylinder at angles-of-attack ranging from 0° to 16° has been conducted in T-38 trisonic blow-down wind tunnel of the Serbian Military Technical Institute. A short description of testing process and measuring equipment is given. Results of a comparison of experimental and numerical results, that primarily include aerodynamic coefficients and pressure distribution, are presented and discussed. Numerical simulations were performed in ANSYS FLUENT with three Reynolds Averaged Navier-Stokes turbulence models of different complexity. Both structured and unstructured grids were generated, tested and compared and the influence of their nature and size has been considered. Base flow at zero angle-of-attack has been investigated in more detail and the accuracy and applicability of the used models is discussed. Computed fluid flow is presented in the form of pressure coefficient and Mach number contours and velocity vectors. PB - Belgrade : Military Technical Institute - VTI C3 - 6th International scientific conference on defensive technologies OTEH 2014 T1 - Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder EP - 60 SP - 55 UR - https://hdl.handle.net/21.15107/rcub_machinery_4455 ER -
@conference{ author = "Komarov, Dragan and Svorcan, Jelena and Isaković, Jovan and Bengin, Aleksandar and Ivanov, Toni", year = "2014", abstract = "Experimental investigation of supersonic flow at Mach number of 2 around a finned ogive cylinder at angles-of-attack ranging from 0° to 16° has been conducted in T-38 trisonic blow-down wind tunnel of the Serbian Military Technical Institute. A short description of testing process and measuring equipment is given. Results of a comparison of experimental and numerical results, that primarily include aerodynamic coefficients and pressure distribution, are presented and discussed. Numerical simulations were performed in ANSYS FLUENT with three Reynolds Averaged Navier-Stokes turbulence models of different complexity. Both structured and unstructured grids were generated, tested and compared and the influence of their nature and size has been considered. Base flow at zero angle-of-attack has been investigated in more detail and the accuracy and applicability of the used models is discussed. Computed fluid flow is presented in the form of pressure coefficient and Mach number contours and velocity vectors.", publisher = "Belgrade : Military Technical Institute - VTI", journal = "6th International scientific conference on defensive technologies OTEH 2014", title = "Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder", pages = "60-55", url = "https://hdl.handle.net/21.15107/rcub_machinery_4455" }
Komarov, D., Svorcan, J., Isaković, J., Bengin, A.,& Ivanov, T.. (2014). Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder. in 6th International scientific conference on defensive technologies OTEH 2014 Belgrade : Military Technical Institute - VTI., 55-60. https://hdl.handle.net/21.15107/rcub_machinery_4455
Komarov D, Svorcan J, Isaković J, Bengin A, Ivanov T. Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder. in 6th International scientific conference on defensive technologies OTEH 2014. 2014;:55-60. https://hdl.handle.net/21.15107/rcub_machinery_4455 .
Komarov, Dragan, Svorcan, Jelena, Isaković, Jovan, Bengin, Aleksandar, Ivanov, Toni, "Numerical and experimental assessment of supersonic turbulent flow around a finned ogive cylinder" in 6th International scientific conference on defensive technologies OTEH 2014 (2014):55-60, https://hdl.handle.net/21.15107/rcub_machinery_4455 .