Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft
When the aircraft is flying at high angle of attack, the local separation of the air flow on the surface of the aircraft, the linear change of aerodynamic force is destroyed, and the maneuverability and stability are reduced to varying degrees, resulting in the aircraft stalling or entering the spin...
| Format: | Article |
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| Language: | zho |
| Published: |
EDP Sciences
2021-06-01
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| Series: | Xibei Gongye Daxue Xuebao |
| Subjects: | |
| Online Access: | https://www.jnwpu.org/articles/jnwpu/full_html/2021/03/jnwpu2021393p650/jnwpu2021393p650.html |
| _version_ | 1797428492037521408 |
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| collection | DOAJ |
| description | When the aircraft is flying at high angle of attack, the local separation of the air flow on the surface of the aircraft, the linear change of aerodynamic force is destroyed, and the maneuverability and stability are reduced to varying degrees, resulting in the aircraft stalling or entering the spin. The stall characteristics and spin characteristics directly affect the safety of the aircraft. In order to analyze the stall and spin characteristics, a full-scale 6-DOF nonlinear high angle of attack dynamic model is established for a two-seater electric high aspect ratio aircraft based on the wind tunnel test data. The stall characteristics of an electric aircraft at high angle of attack are obtained by numerical simulation and analysis. According to the stall characteristics of simulation calculation, flight test is carried out to verify the reliability of numerical simulation, which provides reference for the later analysis of stall/spin test of large aspect ratio series electric aircraft at nonlinear high angle of attack. |
| first_indexed | 2024-03-09T08:59:39Z |
| format | Article |
| id | doaj.art-dfbadc579cb34472872ff8e2fb76d197 |
| institution | Directory Open Access Journal |
| issn | 1000-2758 2609-7125 |
| language | zho |
| last_indexed | 2024-03-09T08:59:39Z |
| publishDate | 2021-06-01 |
| publisher | EDP Sciences |
| record_format | Article |
| series | Xibei Gongye Daxue Xuebao |
| spelling | doaj.art-dfbadc579cb34472872ff8e2fb76d1972023-12-02T12:08:29ZzhoEDP SciencesXibei Gongye Daxue Xuebao1000-27582609-71252021-06-0139365065910.1051/jnwpu/20213930650jnwpu2021393p650Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft0123Liaoning Genral Aviation Acadeing, Shengyang Aerospace UniversityLiaoning Genral Aviation Acadeing, Shengyang Aerospace UniversityLiaoning Genral Aviation Acadeing, Shengyang Aerospace UniversityCollege of Aerospace Engineering, Nanjing University of Aeronations and AstronauticsWhen the aircraft is flying at high angle of attack, the local separation of the air flow on the surface of the aircraft, the linear change of aerodynamic force is destroyed, and the maneuverability and stability are reduced to varying degrees, resulting in the aircraft stalling or entering the spin. The stall characteristics and spin characteristics directly affect the safety of the aircraft. In order to analyze the stall and spin characteristics, a full-scale 6-DOF nonlinear high angle of attack dynamic model is established for a two-seater electric high aspect ratio aircraft based on the wind tunnel test data. The stall characteristics of an electric aircraft at high angle of attack are obtained by numerical simulation and analysis. According to the stall characteristics of simulation calculation, flight test is carried out to verify the reliability of numerical simulation, which provides reference for the later analysis of stall/spin test of large aspect ratio series electric aircraft at nonlinear high angle of attack.https://www.jnwpu.org/articles/jnwpu/full_html/2021/03/jnwpu2021393p650/jnwpu2021393p650.htmlhigh attack anglestall characteristicspinnumerical simulationwind tunnel tests |
| spellingShingle | Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft Xibei Gongye Daxue Xuebao high attack angle stall characteristic spin numerical simulation wind tunnel tests |
| title | Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft |
| title_full | Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft |
| title_fullStr | Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft |
| title_full_unstemmed | Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft |
| title_short | Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft |
| title_sort | research on high attack angle stall and spin characteristics with flight test of a general electric aircraft |
| topic | high attack angle stall characteristic spin numerical simulation wind tunnel tests |
| url | https://www.jnwpu.org/articles/jnwpu/full_html/2021/03/jnwpu2021393p650/jnwpu2021393p650.html |