【作者】 肖志祥； 李凤蔚； 鄂秦；

【Author】 Xiao Zhixiang, Li Fengwei (Institute of Fluids Mechanics, Northwestern Polytechnical University, Xi’an, 710072)

【机构】 西北工业大学114~#流体力学研究所；

【摘要】 采用求解雷诺平均N-S方程类似的方法求解两方程k-g湍流模型方程,即:中心格式加入工粘性的有限体积方法,多步Runge-Kutta显式时间推进,使用当地时间步长及隐式残值光顺等加收敛措施,只是对湍流方程中某些变量做了特殊处理。对M6机翼跨声速和和细长旋成体超声速流场进行数值模拟,计算结果与实验测量吻合良好。本文还给出采用B-L模型,J-K90A及J-K92模型的数值计算结果。可以看出:所有湍流模型在计算附体及小分离流动时,都能得到与实验相差无几的结果,且各湍流模型结果差别不大;对于大攻角、大分离流动,各模型的模拟能力则有所区别。模拟细长旋成体复杂流场时,J-K92和k-g模型能较准确地模拟背风面涡的结构和强度,B-L和J-K90A模型的模拟能力则稍弱。更多还原

【Abstract】 : K-g turbulence model equations are solved using the similar methods that are introduced when solving the Reynolds-Averaged-Navier-Stokes equations. These methods are central finite volume method, explicit multi-step Runge-Kutta algorithm, local time step and implicit residual smooth, etc. Numerical results are presented for the steady transonic flow of wing ONERA-M6 and the supersonic and high incidence missile flow with k-g model. At the same time, these fields are simulated with B-L model, J-K90A and J-K92 models. All models perform well for attached and mildly separated flows. However, for high-angle-of-attack, large separated flows, the numerical results are differently from each other with these models. J-K92 and k-g models match the experimental measurement much better than the other two models. J-K92 and k-g models also improve: 1) the prediction of the vortical shape and strength; 2) the surface pressure predictions due to stronger primary and secondary vortices. The equilibrium model of B-L and J-K90A models can not predict these case as better as J-K92 and k-g models.更多还原