Hypersonic Aerodynamic Heating Engineering Algorithm Research

In this thesis, the aerodynamic heating methods of hypersonic aircrafts are presented. On the base of Prandtl theory, the whole flow field is divided into inviscid flow field out of the boundary layer and viscous field into the boundary layer. Simulating numerically the inviscid flow field and predicting experientially the viscous field, the hypersonic aerodynamic heating algorithms are developed.Firstly, all the aerodynamic heating methods developed by others are analyzed systematically and classified. All these classic methods are synthesized. On this basis, the surface heating is predicted with the above methods. Surface pressure distribution is provided with the engineering methods such as Newton method, tangent-wedge/cone method, and so on. Edge conditions for the boundary-layer solution are obtained from the inviscid flow field solution with constant entropy conditions. The heating rates around some two and three dimension figures are calculated. The results show the high accuracy of the present method.On the base of the existing hypersonic inviscid program, the above method is improved by simulating numerically the inviscid flow field on unstructured triangular grids. Thus, an inviscid-boundary layer method is developed. This method is rapid, effective and capable of complicated figures. The aerodynamic heating rates around blunt cones, double blunt cones, capsule-type vehicles are simulated. The results agree well with the experimental data and Navier-Stokes equation solution. On the same time, the present method costs much less than numerical methods. In a whole, it is applicable to the parametric design.