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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%。
The airfoil’s chattering boundary is an important aerodynamic indicator, which is second only to lift-drag ratio. In transonic flow fields, shock buffeting can have a serious impact on aerodynamic efficiency, handling and structural safety of the aircraft. The determination of the shock buffeting boundary is closely related to the airfoil separation. In this paper, the RANS equation is solved by the steady method, and the reasonable buffeting boundary of the RAE2822 airfoil is determined by the gentle slope of the lift line and the shock position oscillation. Method to determine the chattering boundary after the Mini-TED is turned on. By comparing the aerodynamic performance of the airfoils before and after the Mini-TED is turned on, it can be seen that the Mini-TED can stabilize the shock buffeting near the buffeting attack angle and improve the lift coefficient significantly. The calculation results show that Mini-TED can improve the shock buffering lift coefficient by 9% ~ 13% under the condition of transonic flow.