收敛形进气道数值研究的验证

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。

Verification of the numerical investigations of convergent inlet

The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area,which was called a convergent inlet,are presented in this paper.It is shown that the use of this inlet configuration allows one to reduce the drag and thermal protection of surfaces of a hypersonic engine within the entire range of flight velocities.This is achieved by decreasing the inclination of extemal compression surfaces and reducing the area of the inlet duct and combustor walls.The inlet configuration was constructed on the basis of gas dynamic design methods using the flows of lower dimension.The calculations were performed within the framework of inviscid gas model by the method of finite volumes.The flow and inlet characteristics,taking account of viscosity,were also calculated using the boundary layer equations.The numerical algorithm was verified by calculated and experimental data for a finite-width wedge and extemal compression surface of a convergent inlet.The experimental studies were performed within the Mach number range from 2 to 10.7 and Reynolds number based on the model inlet height of Re=(1～5)106. The numerical and experimental results are in good agreement.These results are also compared with the data for traditional 2D inlets.