Aerodynamic Heating Research For The Head Of Hypersonic Projectile

In this thesis, the aerodynamic heating methods of hypersonic projectile are presented. On the base of Prandtl boundary layer theory, the whole flow field is divided into the inviscid flow filed out of the boundary layer and the viscous field into the boundary layer. Simulating numerically the inviscid flow field and predicting experientially the viscous field, the hypersonic aerodynamic heating algorithms are provided.Firstly, A three-dimensional finite volume scheme which combines a kind of very simple flux splitting with a modified numerical flux method of second order accurate TVD scheme is presented. In order to fit the complex flow field of projectile, an algebraic method grid generation technique is applied. Using this method, we performed numerical simulation for the supersonic inviscid steady flows past a three-dimensional projectile base on gas dynamics Euler equations. The boundary layer edge conditions and the resistance and lift force coefficient in different Mach number and different angle of attack are worked out. Results of the method are in good agreement with the aerodynamics rules.Then, in the viscous fields, based on reference enthalpy theory and semi-empirical formulas, using the boundary layer edge conditions and classic methods, calculated the heating rates and the temperature on the heads of projectile in different Mach number and different angle of attack. The results of this method agree well with the theory data. On the same time, the present method costs much less than numerical methods. In a whole, it is applicable to the parametric design for the heat shield of projectile.