The Development of a New Viscous Shock-Layer Code for Computing Hypersonic Flows around Blunted Body and its Applications

Abstract

A numerical code has been developed to solve the Viscous Shock Layer (VSL) equations for chemically reacting hypersonic flows around a blunted body. The code basically follows the original solution procedure found in other VSL codes, but some specific treatments have been considered and implemented to enhance the accuracy and robustness. In the present article, the governing equations and physical models employed are firstly presented and then the method of solution is described in detail. By using the present code, it has become possible to solve chemically nonequilibrium flows around a hemisphere typically within 1 minute using a conventional personal computer. The accuracy of the code is validated by comparing with the computational results of other VSL/Navier-Stokes codes and available experimental data. It is shown that the difference between Navier-Stokes results in the stagnation heat flux is around 1 % at most for a Reynolds number range from 103 to 105. Further, an approach to solving stagnation streamline profiles both quickly and accurately under the framework of the present VSL algorithm is proposed and its accuracy and availability are examined. Also proposed is an algorithm which computes the free stream properties of ground-based high enthalpy test facilities from the measured stagnation point heat flux and Pitot pressure as an inverse problem of the VSL analysis. The stagnation point analysis method developed is implemented in this algorithm and the accuracy and reliability of this approach are examined.