摘要
采用有限体积法高效求解Ｅｕｌｅｒ方程，成功地计算了全机亚跨超音速迎角可达６０°的绕流流场及空气动力。还就应用求解Ｅｕｌｅｒ方程模拟大迎角分离流动的能力进行了探讨。计算表明，应用本方法能自动捕获大后抓角机翼前缘分离涡，机身分离涡及其相互干扰。计算结果与实验的压力分布及气动力吻合良好。
We, after much thinking over the matter, deem that world's competent aerodynamicists can perform highly satisfactory unsteady flow - field calculations for complex configuration using Euler equations, because they know how to form high- quality grid. In a previous paper[6], the third and first authors discussed how such grid can be formed for the first time in the open literature. We now give a method for and satisfactory results of calculation of flow field and aerodynamic characteristics of complete aircraft's subsonic- transonic- supersonic flow at angles of attack up to 60°.Mathematics involved in using Euler equations to calculate unsteady now is well known and, as we have said, grid- forming was discussed in our previous paper, Ref.[6]. So the point we like to emphasize is that satisfactory results are obtained with our method, which are presented mainly in Fins. 3, 4 and 6. Fig. 3 shows that for a (angle of attack )=24°, the spanwise pressure distributionS computed with our method and suitable grid for a certain chinese aircraft agree rather well with experimental data. Fig. 4 shows that our method can locate clearly vortices on leading edge, on body - wing junction, and on body. Fig. 6 shows that for α up to 60°, computed and experimental values for both Xac/d and CN agree ratherwell.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1996年第2期249-254,共6页
Journal of Northwestern Polytechnical University
基金
国防科工委"八五"气动预研复杂流场计算项目
