Surface Inclination and Heat Transfer Methods for Reacting Hypersonic Flow in Thermochemical Equilibrium

Abstract

For the design of hypersonic configurations heat transfer plays an essential role. At high velocities high-temperature effects have to be taken into account; here a perfect gas assumtion for air leads to major errors concerning the calculation of temperature and heat transfer. Therefore in this work the DLR design tool HOTSOSE is extended to applications for chemically reacting air in thermochemical equilibrium. Computations for various geometries including high-temperature effects were carried our to validate the HOTSOSE code. The results are compared to Euler- and Navier-Stokes-solutions, HOTSOSE perfect gas results and experimental data. For invicid flow, the pressure is calculated from surface inclinationmethods. The respective flow variables are obtained from isentropic relations for perfect gas using piecewise constant gas properties, or from the oblique shock relations, which are solved iteratively.