亚声速大迎角模型试验洞壁干扰修正方法研究  

Research on subsonic wall interference correction for model tests at high angle of attack

作　　者：尹陆平[1] 贺中[2] 于志松 范召林 陈作斌 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000 [2]中国空动力研究与发展中心,四川绵阳621000

出　　处：《流体力学实验与测量》2000年第3期37-41,共5页Experiments and Measurements in Fluid Mechanics

摘　　要：通过测量洞壁附近的压力分布来模拟透气壁试验段的洞壁边界条件，采用数值求解Euler方程的方法模拟模型在风洞中的绕流场，然后将洞壁边界条件用远场边界条件替换，用同样方法计算出模型在自由流中的绕流场，从而计算出洞壁干扰对模型的绕流场和气动力的影响。针对大迎角模型的洞壁干扰问题的特殊性，采用重叠网格技术，对飞机大迎角标模和SB03模型进行了亚声速大迎角的洞壁干扰计算与修正。The correction method for 3D wall interference at subsonic speeds was developed and applied to the case of high angle of attack . There are two steps in this procedure .First, the boundary conditions of test section with perforated walls are simulated by measuring pressure distribution near the wall, and the flow field around model in the wind tunnel is simulated by solving Euler equation. Second, the flow field around the model in the free flow is solved in the same way, with the boundary conditions of the far flow field taking place of the boundary conditions of the wall. The difference between them is the wall effects. As for the wall interference of the model at high angle of attack, the overlapping grid technique is presented in this paper. The experimental results of the highα reference model and SB03 model in the FL21 wind tunnel are corrected and the corrected results are quite satisfying.

关 键 词：洞壁干扰 EULER方程 重叠网格 风洞试验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程] V211.3