高超声速飞行器表面气动热和粘性摩擦力计算

基金项目:

国家自然科学基金

详细信息

The calculations of aerodynamic heating and viscous friction forces on the surface of hypersonic flight vehicle

摘要: 本文给出了高超声速飞行器表面摩阻和传热系数(斯坦顿数)的计算结果.采用两种方法平面切面法亦即二维边界层近似法和工程方法计算了飞行器高超声速绕流的粘性效应,并对两种方法的计算结果作了仔细的比较.由文可见,对于在稠密大气层内,沿轨道运行头速度恒定的高超声速有翼飞行器,能够用本文所采用的两种方法计算其表面摩阻和热载荷.此二法可成功地应用于绕复杂形状物体的流动参数计算.
- 高超声速飞行器 /
- 表面摩阻 /
- 传热 /
- 数值计算 /
- 工程计算
Abstract: In this paper the results of calculations of the coefficients of skin friction and heat transfer(Stanton number) on the surface of hypersonic flight vehicle are presented.Two methods,namely"The plane sections method" i.e. 2D boundary layer approximation and "The engineering method", are used for calculation of viscous effects at hypersonic flow around the flight vehicle. Calculation results of both methods are presented and compared in detail. It can be seen from this article that the two methods have demonstrated the working capacity for calculation of frictional force and thermal load on surface of a hypersonic winged flight vehicle, which moves in dense atmospheric layers on a trajactory with stationary values of velocity head. They can successfully be applied to parametric calculations for flow around bodies of complex form.