Hypersonic and high temperature gas dynamics anderson pdf
Front Matter - High Enthalpy Gas Dynamics - Wiley Online LibraryArabian Journal for Science and Engineering. The aim of this work is to develop a new numerical calculation program to determine the effect of the stagnation temperature on the calculation of the supersonic flow around a pointed airfoils using the equations for oblique shock wave and the Prandtl—Meyer expansion, under the model at high temperature, calorically imperfect and thermally perfect gas, lower than the dissociation threshold of the molecules. The specific heat at constant pressure does not remain constant and varies with the temperature. The new model allows making corrections to the perfect gas model designed for low stagnation temperature, low Mach number, low incidence angle and low airfoil thickness. The stagnation temperature is an important parameter in our model.
Compressible Flow: Mach Number, Characteristic Mach Number and Stagnation properties
Anderson - Hypersonic and High Temperature Gas Dynamics