AN ENGINEERING INVISCID-BOUNDARY LAYER METHOD FOR CALCULATION OF AERODYNAMIC HEATING IN THE LEEWARD REGION

An engineering method has been developed for the prediction of aerodynamic heating of hypersonic bodies. This method is capable of rapidly predicting the heat flux in the leeward region. This is achieved through the determination of the streamlines in the leeward region. The modified form of Maslen’s second order relation is employed, which calculates the pressure in the shock layer explicitly. The inviscid outer flow within the shock layer is solved first. The calculated solution is then used to determine the flow properties at the boundary layer edge and the orientation of the surface streamlines. Boundary layer equations, written in the streamline coordinates, are integrated along the surface to obtain the rate of heat transferred to the body surface. The present method is an inverse method in which the body shape is obtained according to the shape of the shock. In general, inviscid-boundary layer engineering methods accurately calculate the orientation of streamlines in the windward region only, and therefore they are not usually applicable in the leeward region. In the present study, a new method is proposed to determine the orientation of the surface streamlines in the leeward region. Using the present technique, three-dimensional hypersonic flow is solved fast and easy all around a cone. The obtained results show that the corrections presented in this study excellently extend the application of the method to the leeward region.