A vortex lattice method application in aerodynamic analysis and design of light aircraft
Апстракт
In initial stages of aircraft aerodynamic design, it is common practice to apply fairly simple but reliable computer packages, that enable engineers to perform a large number of test runs in a reasonably short time. This paper is mainly focused on the tests done by such software, based on 3D vortex-lattice method, with an aim to verb its capabilities to give results that properly coincide with the existing airplane's data. For software reliability tests, the popular domestic Utva-75 light aircraft has been selected, for which a wide scope of wind tunnel test results exist. Since the applied computational model is based on inviscid flow concept, effectiveness of the flaps and control surfaces, deflected to angles larger than 5 degrees, are inherently overestimated. In order to compensate for the omitted boundary layer influence and separation effects, a set of calibration options has been properly applied, the non-linear calibration diagrams for their effectiveness and circulation influ...ence have been derived and very good agreements with wind tunnel data have been achieved. The actual aim of defining software calibration functions is to enable efficient prediction and optimization of the large number of aerodynamic characteristics for a new airplane of the same category, during the first stages of its conceptual analysis.
Кључне речи:
wind tunnel tests / software calibration / CFD analysis / aerodynamic designИзвор:
Sixth International Symposium About Forming and Design in Mechanical Engineering, 2010, 85-92Издавач:
- Univ Novi Sad, Fac Tech Sci, Adeko, Novi Sad
Колекције
Институција/група
Mašinski fakultetTY - CONF AU - Stefanović, Zoran AU - Kostić, Ivan PY - 2010 UR - https://machinery.mas.bg.ac.rs/handle/123456789/1122 AB - In initial stages of aircraft aerodynamic design, it is common practice to apply fairly simple but reliable computer packages, that enable engineers to perform a large number of test runs in a reasonably short time. This paper is mainly focused on the tests done by such software, based on 3D vortex-lattice method, with an aim to verb its capabilities to give results that properly coincide with the existing airplane's data. For software reliability tests, the popular domestic Utva-75 light aircraft has been selected, for which a wide scope of wind tunnel test results exist. Since the applied computational model is based on inviscid flow concept, effectiveness of the flaps and control surfaces, deflected to angles larger than 5 degrees, are inherently overestimated. In order to compensate for the omitted boundary layer influence and separation effects, a set of calibration options has been properly applied, the non-linear calibration diagrams for their effectiveness and circulation influence have been derived and very good agreements with wind tunnel data have been achieved. The actual aim of defining software calibration functions is to enable efficient prediction and optimization of the large number of aerodynamic characteristics for a new airplane of the same category, during the first stages of its conceptual analysis. PB - Univ Novi Sad, Fac Tech Sci, Adeko, Novi Sad C3 - Sixth International Symposium About Forming and Design in Mechanical Engineering T1 - A vortex lattice method application in aerodynamic analysis and design of light aircraft EP - 92 SP - 85 UR - https://hdl.handle.net/21.15107/rcub_machinery_1122 ER -
@conference{ author = "Stefanović, Zoran and Kostić, Ivan", year = "2010", abstract = "In initial stages of aircraft aerodynamic design, it is common practice to apply fairly simple but reliable computer packages, that enable engineers to perform a large number of test runs in a reasonably short time. This paper is mainly focused on the tests done by such software, based on 3D vortex-lattice method, with an aim to verb its capabilities to give results that properly coincide with the existing airplane's data. For software reliability tests, the popular domestic Utva-75 light aircraft has been selected, for which a wide scope of wind tunnel test results exist. Since the applied computational model is based on inviscid flow concept, effectiveness of the flaps and control surfaces, deflected to angles larger than 5 degrees, are inherently overestimated. In order to compensate for the omitted boundary layer influence and separation effects, a set of calibration options has been properly applied, the non-linear calibration diagrams for their effectiveness and circulation influence have been derived and very good agreements with wind tunnel data have been achieved. The actual aim of defining software calibration functions is to enable efficient prediction and optimization of the large number of aerodynamic characteristics for a new airplane of the same category, during the first stages of its conceptual analysis.", publisher = "Univ Novi Sad, Fac Tech Sci, Adeko, Novi Sad", journal = "Sixth International Symposium About Forming and Design in Mechanical Engineering", title = "A vortex lattice method application in aerodynamic analysis and design of light aircraft", pages = "92-85", url = "https://hdl.handle.net/21.15107/rcub_machinery_1122" }
Stefanović, Z.,& Kostić, I.. (2010). A vortex lattice method application in aerodynamic analysis and design of light aircraft. in Sixth International Symposium About Forming and Design in Mechanical Engineering Univ Novi Sad, Fac Tech Sci, Adeko, Novi Sad., 85-92. https://hdl.handle.net/21.15107/rcub_machinery_1122
Stefanović Z, Kostić I. A vortex lattice method application in aerodynamic analysis and design of light aircraft. in Sixth International Symposium About Forming and Design in Mechanical Engineering. 2010;:85-92. https://hdl.handle.net/21.15107/rcub_machinery_1122 .
Stefanović, Zoran, Kostić, Ivan, "A vortex lattice method application in aerodynamic analysis and design of light aircraft" in Sixth International Symposium About Forming and Design in Mechanical Engineering (2010):85-92, https://hdl.handle.net/21.15107/rcub_machinery_1122 .