A Discussion about the Difficulty of the Numerical Solution of 3DVSL Equations in the Leeward Region

An approximate three-dimensional method has been developed to claculate viscous hypersonic flow of perfect gas over blunt-nosed bodies. In this method a modifide form of Maslen's second-order pressure expression is used instead of the normal momentum equation. In the present method, the 3DVSL equations are solved in a streamline curvilinear coordinate system. Using this coordinate, the method can predict aerodynamic heating in the leeward region, howevwr a difficulty occurs in the circumferential prediction of head transfer distributon close to the leeward line. This paper discusses this difficulty and the methods to overcome it.

Keywords:

Aerodynamic Heating , viscous chock layer , streamline , leeward