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本文分析了在FL-8和FL-5风洞完成的一个三角翼飞机模型展向吹气全模测力和机翼半模流态实验中的襟翼展向吹气的气动效果,并且与同一模型在同一风洞中所得到的吹气襟翼结果进行了比较。 明确了在大偏度襟翼上展向吹气,产生的集中涡是“肩线涡”,而不是“喷气涡”。指出涡控制是襟翼展向吹气增升的重要原因,而不应单纯归结为边界层控制问题。通过对喷嘴形状和参数的优选,实现了用当前发动机实际能提供的小的吹气动量系数(约0.012)取得与吹气襟翼相近的升力增量。从而有可能显著地改善飞机的着陆性能。首次采用了“两叉喷嘴”,使整个襟翼面的流动获得改善。由于这项技术结构简单、重量轻、不占用机翼内部空间、生存力强,因此可望成为飞机设计中一种可供选用的动力增升方案。
In this paper, the aerodynamic effects of full-scale inflatable blowing and flapping forward blown air in a half-mold fluid flow experiment of a delta wing aircraft completed at FL-8 and FL-5 wind tunnels are analyzed. The same model obtained in the same wind tunnel blowing flap results were compared. Explicit in the large-scale flaps on the exhibition blowing, the resulting vortex is “shoulder-line vortex”, rather than “jet vortex.” It is pointed out that vortex control is an important reason for the flare expansion to inflate, and should not simply be attributed to the boundary layer control problem. By optimizing the shape and parameters of the nozzle, it is possible to achieve a lift increase similar to that of an inflatable flap with a small blow momentum coefficient (about 0.012) actually provided by the current engine. As a result, it is possible to significantly improve the landing performance of the aircraft. For the first time, a “two-pronged nozzle” was used to improve the flow across the flaps. Due to its simple structure and light weight, the technology does not occupy the internal space of the wing and has strong survivability. Therefore, it is expected to be an alternative power-lifting solution in aircraft design.