基于工程转捩模型的高超声速进气道特性

In order to study the variation of the performance parameters of a hypersonic air inlet with the flight height, free stream turbulence intensity and free stream Mach number, and the influence of the boundary layer transition on the compression surface on air inlet performance, a series of numerical simulations were conducted by using the γ-Re_θ transition model developed in a in-house HGFS and the flow phenomena and mechanisms were analyzed. Firstly, the improved γ-Re_θ transition model implemented in the HGFS code was verified using a simplified model of an air inlet compression surface. Secondly, a hypersonic air inlet with isentropic compression surface was studied the effect of flight height and Mach number on parameters such as the transition location. Main conclusions are as follows: with the increase of the flight height, transition location of the boundary layer moves downstream on the compression surface, and the total pressure recovery coefficient decreases. Compared with the ground surface state, at the design flight height, the transition location moves downstream for about 0.525 m, the boundary layer thickness increases by about 73%, and the total pressure recovery coefficient decreases by 3.2%. About 0.5% magnitude change of the inflow turbulence intensity will contribute to 0.2 m movement of the transition location. However, the influence of turbulence intensity on the total pressure recovery coefficient is quite small.