半模试验翼身组合体垫块的数值模拟分析  

Navier-Stokes simulation of the stand-off on the flow over a fuselage-wing combination

作　　者：李艳亮[1] 董军[1] 杨希明[1] 

机构地区：[1]中国航空工业空气动力研究院,辽宁沈阳110034

出　　处：《空气动力学学报》2009年第1期73-77,118,共6页Acta Aerodynamica Sinica

摘　　要：采用数值模拟方法研究存在风洞侧壁边界层影响时垫块厚度和修型对翼身组合体气动特性的影响。本文采用Jameson中心有限体积、多步Runge-Kutta时间推进格式求解三维可压、雷诺平均Navier-Stokes方程,引入Baldwin-Lomax湍流模型,分析了垫块厚度和修型对DLR-F4翼身组合体半模型气动力和局部流场的影响。通过本文计算得出的结论对于跨声速半模型风洞试验垫块优化设计具有重要的指导意义,能更好地提高风洞试验数据的精准度和试验技术水平。For a fuselage-wing combination with a stand-off, numerical solutions of the Reynolds-averaged Navier-Stokes equations by finite volume methods using Runge-Kutta time-stepping schemes are shown and the Baldwin-Lomax turbulence model is selected in this paper. The influences of the stand-off height and shape-trimming are examined, and results are presented herein. In this paper, investigations on the stand-off by CFD can provide a better stand-off for the semi-span model testing, improve the data accuracy and precision of testing techniques, reduce the workload or cost and supply referenees to the wind tunnel testing.

关 键 词：洞壁边界层 Navier—Stokes方程 有限体积法 翼身组合体 半模试验 垫块厚度 垫块修型 

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]