摘要
介绍用于近似计算绕三维尖体无粘流激波薄层的二层模型。本法以数值确定激波的位置，在计算不同结构形状物体的空气动力特性时能确定气体动力载荷的近似值。采用这种方法实际上排除了超高速理论中其他已知方法对尖体几何形状所加的约束。与通常的空气动力特性曲线相结合，此法可获得在设计和非设计飞行状态下飞行器整个系统的近似绕流流场，且可优化其空气动力结构。
Present the two layer model of thin shock layer for approximate calculation of the inviscid flow over 3 d sharp bodies.A position of shock wave is defined numerically in this method.The method allows to define approximate values of gas dynamic loads for calculation of aerodynamic characteristics on different body configurations.The using of this method practically removes restrictions on geometry of a sharp body,which exists for other known methods of hypersonic theory.Together with general aerodynamic characteristics,the method allows to obtain approximate flow fields around integrated schemes of vehicles at design and undesign regimes of the flight,and also it allows to make optimization their aerodynamic forms.
出处
《流体力学实验与测量》
CSCD
1999年第2期73-78,共6页
Experiments and Measurements in Fluid Mechanics
关键词
空气动力
无粘流
数值模拟
高超声速
approximate calculation
aerodynamic characteristics
high supersonic velocity
inviscid flow
