Numerical study on influence of high temperature effects on pitch rotation derivative for hypersonic reentry vehicles

Influence of high temperature effects on pitch rotation derivative for hypersonic reentry vehicles is investigated numerically. Pitch rotation derivative is calculated with quasi-steady method based on solving the chemical reaction Navier-Stokes equations formulating in the rotating noninertial reference frame. Firstlythe simulation ability of numerical code is validated for the hypersonic flow around HB-2 with high temperature effects. The computational results of the pressure along the wall agree well with the experiments. Secondlythe reliability of the quasi-steady method is verified by the comparision of the calculated results with experimental data for the dynamic derivatives of HBS configuration. Finallythe numerical experiments of the high temperature effects on pitch rotation derivative are performed based on HBS configuration with the hypersonic reentry condition. It is revealed thatalthough the chemical reacting gas model can greatly change the computational results of the pitching momentsthe pitch rotation derivative calculated by the chemical reacting gas model is not more than 7% different from the calorically perfect gas results. The change of the pitch moments and pitch rotation derivative is caused by both the variation of the specific heat with temperature and the chemical reactions. In additiondifferent chemical reacting gas models and the wall catalytic effects have little influence on the computational results of the pitching moments and pitch rotation derivative.