一种跨声速风洞透气壁模型的数值模拟研究  

Numerical Investigation on a Porous Wall Model for the Transonic Wall Interference

作　　者：牟斌[1] 王建涛[1] 黄勇[1] 肖中云[1] 刘大伟[2] MOU Bin;WANG Jiantao;HUANG Yong;XIAO Zhongyun;LIU Dawei(Computational Aerodynamics Institute,China Aerodynamic Development and Research Center,Mianyang 621000,China;High Speed Aerodynamics Institute,China Aerodynamic Development and Research Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000 [2]中国空气动力研究与发展中心高速空气动力研究所,绵阳621000

出　　处：《航空工程进展》2021年第1期13-23,共11页Advances in Aeronautical Science and Engineering

摘　　要：宽体客机巡航状态、阻力发散马赫数状态以及俯冲状态的绕流均属于跨声速流动,风洞试验过程中由于试验段壁板的存在,模型与洞壁均可能产生较强的激波,并诱发复杂的相互干扰,进而呈现出强烈的非线性耦合现象。针对宽体客机标模在FL-26风洞中试验的洞壁干扰情况,提出一种基于透气壁模型的数值模拟方法;基于该方法研究0.8≤Ma≤0.92范围内的模型洞壁干扰耦合效应。结果表明:与基于壁压信息法的数值模拟方法相比,采用透气壁模型方法不需要测试数据,能够较好地模拟孔壁流动对宽体客机升力系数曲线的影响,同时也给阻力带来较大的修正量。Flows passing a wide-body aircraft at cruising,drag divergence or diving status are transonic.When the aircraft model is tested in a transonic wind tunnel,strong shock waves may be induced due to the tunnel wall and the model,and incur complex interference as a strong nonlinear coupling phenomenon.In order to investigate the wall interference to the standard model of a wide-body aircraft mounted in the FL-26 wind tunnel,a numerical simulation method based on a porous wall model is developed.Based on this wall model method,the coupling effect of wall interference at Mach numbers ranging from 0.8 to 0.92 is studied.Comparing with the wall pressure information method,results with the porous wall model indicate positive effect of the porous wall flow on the lift coefficient of wide-body aircraft,as well as more modification to drag coefficient.

关 键 词：宽体客机 洞壁干扰 数值计算 风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]