| 后掠机翼的前缘吸力 |
| |
| 引用本文： | 李震浩. 后掠机翼的前缘吸力[J]. 空气动力学学报, 1989, 7(1): 1-11 |
| |
| 作者姓名： | 李震浩 |
| |
| 作者单位： | 中国直升飞机设计研究所 |
| |
| 摘 要： | 本文应用三元亚音速升力面理论求出了后掠翼前缘附近的流场。该流场是一连续部分与一奇异部分之和。由此解析地导出了前缘吸力的公式,从而证明了在空气动力学中长期广泛应用的前缘吸力仅取决于垂直于前缘的速度性质的假设是正确的。本文并证明该假设与前缘吸力的公式可推广到非定常可压缩流场。
|
| 关 键 词： | 后掠机翼 流场 亚音速 空气动力学 |
ON THE UNSTEADY LEADING EDGE SUCTION OF A SWEPTBACK WING |
| |
| Li Zhenhao. ON THE UNSTEADY LEADING EDGE SUCTION OF A SWEPTBACK WING[J]. Acta Aerodynamica Sinica, 1989, 7(1): 1-11 |
| |
| Authors: | Li Zhenhao |
| |
| Affiliation: | Chinese Helicopter Research and Development Institute |
| |
| Abstract: | The unsteady flow field near the leading edge of an oscillating sweptback wing is obtained by using 3-D subsonic lifting surface theory. It is shown that this flow field is composed of two parts: 1) a continuous part and 2) a singular part. The formula of leading edge suction is derived theoretically. The famous assumption, i.e. the leading edge suction depends only on the nature of the velocity at and perpendicular to this edge, has been substantiated analytically and extended to unsteady flow. |
| |
| Keywords: | subsonic aerodynamics flow field sweptback wing |
| 本文献已被 CNKI 维普 等数据库收录！ |
