Hypersonic boundary layer flow and heat transfer analysis of compressible fluid over a permeable wall with gas injection

Abstract

Gas injection is an important way to reduce the aerodynamic heat of hypersonic aircraft. However, due to the complexity of aerodynamic heat, there is no universal theoretical prediction method. In the present work, the laminar boundary layer flow and heat transfer of compressible fluid over a permeable wall with uniform injection is studied analytically. According to the similar principle of momentum transfer, energy transfer and mass diffusion, it is assumed that viscosity, thermal conductivity and diffusion coefficient are the same nonlinear power functions of temperature. In order to reveal the influences of injection intensity on flow and heat transfer, the nonlinear hypersonic boundary layer governing equations are established. By suitable similarity transformation, the partial differential equations are transformed into coupled ordinary differential equations that are solved by homotopy analysis method (HAM). Some new phenomena have been revealed. The wall temperature decreases significantly with increasing gas injection intensity. The larger the incoming Mach number, the higher the wall temperature. Furthermore, the shear force near the leading edge of flat plate has been obtained under the condition that the inlet Mach number is 5.