DLR-F4翼身组合体的阻力计算

为了考察自行研发的CFD软件的计算能力和阻力计算精度，本文采用LU—SGS方法、MUSCL差分格式和Baldwin—Lomax代数湍流模型，数值模拟了AIAA阻力计算工作室提供的DLR—F4翼身组合体的绕流流场，综合分析了easel和case2的气动力的计算结果，并与NASA Christopher L．Rumsey采用CFL3D6．0和AFRL/VAAC Don W．Kinsey采用Cobalt60提供的两组计算结果以及AGARD提供的两种不同风洞的测力试验结果作了比较。计算结果表明，本文计算精度与国外CFD软件相当。为了提高激波，边界层干扰的模拟精度，今后要重点加强湍流模型的应用研究。

Drag prediction of DLR-F4 from AIAA drag prediction workshop

The purpose of this paper is to evaluate capacity of our CFD software for drag prediction .Numerical simulation of the DLR-F4 wing-body configuration from AIAA drag prediction workshop are performed in present paper. The numerical method adopted is LU-SGS +MUSCL scheme and Baldwin-Lomax algebraic turbulence model, . The aerodynamic coefficients of Case1 and Case2 , required by the workshop, are analyzed, the comparison is also made with the numerical results using CFL3D6.0 ,Cobalt60 and two sets of experimental results from AGARD. Generally, the precision of our CFD software for drag prediction is similar to the corresponding CFD software, such as CFL3D6.0 ,Cobalt60 ,and the main deficiency of our CFD software is the application of different turbulent models.