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介绍一种新型的、具有最小喉道面积的三维高超声速进气道 (称之为收敛形进气道 )的数值和实验研究结果。表明使用这种形式的进气道 ,在整个飞行速度范围内可以降低阻力和高超声速发动机表面的热防护要求 ,通过降低外压缩表面的倾斜度和减少进气道及燃烧室壁的面积就可以做到这一点。在采用低维次流动的气体动力设计方法的基础上设计成这种形式的进气道。计算是在无粘气体模型构架内用有限体积法进行的。同时用边界层方程计算出计及粘性的气流特性和进气道特性。数值算法是通过收敛形进气道的有限宽楔形外压缩表面的计算和实验数据来验证的。进行实验研究的马赫数M=2～ 1 0 7,基于模型进气道高度的雷诺数Re=( 1～ 5) × 1 0 6。数值计算与实验结果一致性很好。这些结果也和通常的二维进气道的数据作了比较。
A new type of three-dimensional hypersonic inlet with the smallest throat area (called the convergent inlet) is presented. The numerical and experimental results are presented. Shows that the use of this type of air intake reduces the drag and heat protection requirements of hypersonic engine surfaces over the entire flight speed range by reducing the slope of the outer compression surface and reducing the area of the air intake and combustion chamber walls Make it happen. This type of intake port is designed on the basis of a gas-dynamic design method that uses low dimensional subsurface flow. Calculations are performed using the finite volume method in a viscous gas-free model. At the same time, the boundary layer equations are used to calculate the airflow characteristics and inlet characteristics of the viscous flow. The numerical algorithm is validated by calculating and experimentally converging the finite wide wedge outer compression surface of the inlet. The experimental Mach number M = 2 ~ 1 0 7, Reynolds number Re = (1 ~ 5) × 1 0 6 based on the model inlet height. Numerical calculation and experimental results are in good agreement. These results are also compared with the usual two-dimensional air intake data.