摘要
用数值方法对比分析了NACA0012翼型在微小后缘装置(Mini-TED)打开前后跨声速气动性能的变化,并对其增升机理进行了初步分析。数值结果表明,Mini-TED可以将翼型上表面激波位置大幅度后移,大大提高翼型的升力。在小迎角条件下,Mini-TED后面存在一个由3个旋涡构成的稳定流动结构,正是这个旋涡结构改变了后缘库塔条件,导致上翼面激波位置的变化,进而大幅度提高了升力。当迎角增加后,后缘旋涡结构中的一个旋涡逐渐上移并与激波诱导的分离区合并,从而加速了翼型上表面分离。由于Mini-TED使得迎风面积增加,因而导致升力和阻力同时大幅上升,但总体上看仍然能够大幅度提高升阻比,证明Mini-TED后缘设计是一种极有潜力的新型高升力装置。
To explore the flow mechanism behind the new type of mini-trailing edge device （Mini-TED） which is first suggested in AWIATOR project, this article compares the change of the transonic performance of NACA0012 with and without Mini-TED. The numerical analysis shows that the shock wave position is postponed greatly when Mini-TED is open, which leads to the increase of the airfoil lift. The mechanism behind this phenomena is that there exists a steady flow structure composed of three vortex behind the trailing edge at low angle of attack, which changes the Kutta condition and therefore the shock wave position. Based on this mechanism, it is reasonable to expect a increase of the drag divergence Mach number. When the angle of attack increases, the three vortex structure destructures and emerges with the separated zone induced by the shock wave, which may lead to the increase of the drag. However, the lift-drag ratio increases greatly, which proves that Mini-TED is a promising high lift device with great potential.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2009年第8期1367-1373,共7页
Acta Aeronautica et Astronautica Sinica
基金
上海市重点学科建设项目(B302)
