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由于Boussinesq涡粘性假设的湍流模型在一些流动中如激波分离流中预测失真,本文介绍一种基于完全雷诺应力方程的微分雷诺应力模型(DRSM),应用压缩性修正和改进耗散率方程构造出应用于可压流体的可实现DRSM,SSG压应力模型测试了两组参数。将其应用于ONERA M6机翼在跨声速大攻角的计算,结果表明DRSM能更好地模拟激波位置和流动分离。
Since the Boussinesq eddy viscosity assumption turbulence model predicts distortions in some flows, such as the shock separation flow, a differential Reynolds stress model (DRSM) based on a complete Reynolds stress equation is introduced in this paper. Compressive correction and improved dissipation rate equations are constructed Two sets of parameters were tested for the achievable DRSM, SSG compressive stress model applied to compressible fluids. Applying it to the ONERA M6 wing at large transonic attack angles, the results show that the DRSM can better simulate shock location and flow separation.