【摘要】 用三阶MUSCL TVD格式解三维可压缩流动N-S方程组,湍流模式为Sparlart-Allmaras模型,数值模拟了来流马赫数Ma∞=0.96、攻角α=0°和Ma∞=0.91、攻角α=2°条件下的旋成体弹丸跨声速流场,获得的弹体表面压力系数分布数值结果与实验数据吻合良好。同时还给出了流场的马赫数等值线、弹丸底部流线分布图谱,并对计算的弹底涡流结构作了扼要的分析。更多还原

【Abstract】 The three-dimensional compressible flow Navier-Stokes equations have been solved using the third-order MUSCL type TVD scheme. The Sparlart-Allmaras turbulence model is employed.The flowfield of the spinning projectile under the transonic speed conditions of Ma∞= 0.96 , the angle of attack α=0° and Ma∞= 0.91 , the angle of attack α = 2°is numerically simulated. The results of pressure coefficient distributions on the projectile surface are in agreement with the test data. In addition, the Mach number contours and the streamlines of the projectile base are given. The computed vortex structures in the projectile base are pre-sented and analyzed.更多还原