S形进气道流场数值模拟

Numerical simulation of flow field for supersonic S-shaped inlet

考虑了外流场对进气道内部气流流动状况的影响,将S形进气道的内外流场进行综合求解。采用有限容积法,求解全三维N-S方程。将数值计算结果与实验数据进行了对比,分析了机头/前机身对进气道入口气流的影响,同时也分析了进气道入口激波分布和进气道内部气流流动情况,以及出口流场的气流品质。从计算结果看该进气道损失比较大,出口截面最高的总压恢复系数为0.96;二三级调解板可以有效地引导气流,避免第一转弯处的大面积回流。

Outer flow of the inlet wascomputed in consideration of inner flow. Three-di-mensional Navier-Stokes equations were solved by finite volume method. The predictions were compared with experimental data. Also the influence of airframe/head on entrance of inlet flow fields, the distribution of shock-wave and the behavior of the inner flow were analyzed. The results showed that air can be effectively introduced into inlet by the second and third control plans, avoiding large area reverse flow at first bent, but the loss of the inlet was large, the highest of the total pressure recovery coefficient was 0.96.