基于尾迹面法的气动力积分技术研究  

Investigation of aerodynamic integration techniques based on wake integration

作　　者：王元元[1] 张彬乾[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《应用力学学报》2010年第2期264-268,共5页Chinese Journal of Applied Mechanics

摘　　要：基于Roe的空间离散格式,以绕ONERAM6、LANN机翼流场为算例,分别以Euler和N-S方程为主控方程,对尾迹面法气动力积分技术进行初步探讨,重点讨论了尾迹面位置对气动力的影响。引入不同尾迹插值方法,研究了不同插值方法对气动力积分结果的影响,为气动力的精确性计算提供了气动分析平台。研究结果表明:当尾迹面的位置处于机翼后0.5到1.5倍平均气动弦范围内时,此方法具备较好的气动力积分精度;与中心插值相比,基于格心距离加权的流动参数插值有更高的积分精度。In this paper,taking transonic flow of ONERA M6 wing,LANN wing as typical computational examples,Euler/N-S equation are used respectively.The wake integration technique is investigated based on the Roe scheme,the effects of the position of the wake surface and the different interpolation techniques on the lift-drag are investigated primarily,a platform for accurate aerodynamic computing is provided.The results indicate that wake integration has fine precision when the position of wake surface is within 0.5 to 1.5 times mean aerodynamic chord behind the wing.Flow parameter interpolation based on weighted grid cell center distance is more precise than central scheme.

关 键 词：尾迹面积分法 NAVIER-STOKES方程 尾迹面插值 Roe近似黎曼解 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]