摘要
以M6机翼半模型为算例,采用数值方法模拟垫块法风洞试验洞壁边界层及垫块厚度对半模型试验结果的影响。控制方程采用全场三维可压、雷诺平均的Navier-Stokes方程;计算格式采用Jameson中心有限体积、多步Runge-Kutta时间步长格式进行求解;湍流模型采用Baldw in-Lomax模型。通过本文的研究,可以为跨声速风洞半模型试验垫块厚度的选取提供计算方法和设计依据。
Transonic viscous flows around a semi -span wing mounted in the wind tunnel sidewall are simulated by a ceU-centered finite volume scheme that is based on the integral form of three-dimensional Navier- Stokes equations. The influence of the stand - off height is examined, and results are presented herein. By comparing the surface pressure distributions and the lift or drag coefficients, the better stand-off is obtained for the semi-span model in the transonic tunnel.
出处
《航空计算技术》
2006年第6期36-39,共4页
Aeronautical Computing Technique
