摘要
翼型的抖振边界是一项重要的气动指标,它的重要性仅次于升阻比。在跨声速流场中,激波抖振对飞行器的气动效率、操控和结构安全均会产生严重影响。激波抖振边界的确定与翼型气流分离密切相关,本文采用定常方法求解RANS方程,以升力线斜率平缓及激波位置振荡为判据,确定RAE2822翼型的合理抖振边界,并以同样的方法确定微小后缘装置(Mini-TED)打开后的抖振边界。通过Mini-TED打开前后翼型的气动性能对比可以看出,Mini-TED在抖振攻角附近能起到稳定激波抖振的同时显著提高升力系数。本文计算结果表明Mini-TED在跨声速来流条件下可将激波抖振升力系数提高9%～13%。
Airfoil buffet boundary is an important aerodynamic parameter which is second only to the lift-drag ratio. By using various steady aerodynamics parameters of the reversal in shock wave as the basic criteria, the buffet boundary of transonic airfoil RAE2822 in transonic flow conditions can be determined by solving steady Reynolds-averaged Navier-Stokes equation. Using the same method to find the buffet boundary of RAE2822 with Mini-TED and comparing it with the buffet boundary of the basic RAE2822 air- foil, the results show that the Mini-TED can significantly increase the lift coefficient near the buffet onset angle, stabilize the buffet onset angle, thereby achieving the purpose of expanding the buffet boundary. The buffet onset lift coefficient in this case can be increased by 9%o ~13 %.
出处
《力学季刊》
CSCD
北大核心
2012年第3期404-413,共10页
Chinese Quarterly of Mechanics
基金
中国航空科学基金(2009ZA38001)
