摘要
Based on the potential theory, a linearity combination of the disturbance flow field generated by the uncompressible vortex part was applied in the computation of separate vortex flow. As the computation of single wing-surface, combined wing-surfaces and FC-1 aircraft showed, this low speed and high AOA aerodynamic computing method given in this paper is effective in the range of stall AOA.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 541-545 |
| 页数 | 5 |
| 期刊 | Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica |
| 卷 | 25 |
| 期 | 4 |
| 出版状态 | 已出版 - 12月 2007 |