Compressible Flow: Mach Number, Characteristic Mach Number and Stagnation properties
John D. Anderson
Arabian 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. The airfoil should be pointed at the leading edge to allow an attached shock solution to be seen. The airfoil is discretized into several panels on the extrados and the intrados, placed one adjacent to the other.
John D. Anderson Jr. He enrolled at the University of Florida in Gainesville in approximately In , he earned a bachelor's degree in Aeronautical Engineering with high honors. In , Anderson earned his Ph.