The Aerothermal Numerical Simulation Research Of Hypersonic Vehicles

When hypersonic vehicles fly in the atmosphere, severe aeroheating problems will be encountered. Though at the high altitude, aeroheating decreases due to lower gas density, the grim situation of aeroheating on the vehicle surface is still not optimistic. With the urgent need for the long time hypersonic flight, it is quite important to reserch.Computational Fluid Dynamics (CFD) method is adopted in the numerical simulation of hypersonic aeroheating computations at high altitude. In the slip regime, the continuum model is still valid, and the impact of the slip effect most appears near the wall. Three dimensional compressible Navier-Stokes equations are still used as the control equations, and they are solved using finite volume method with M-AUSMPW+ scheme and the LU-SGS implicit method. Slip boundary conditions is added to modify the impacts of velocity slip and temperature jump caused by the rare atmosphere.Else, three slip boundary conditions are analysed in this paper. Their accuracy, scope of application, merits and demerits are compared. By analysis for the simulation of simple slip fow, the Maxwell slip condition has more advantages to adopt in the hypersonic aeroheating simulation.The dissertation has considered the criterion for viscous mesh, the influence of rarefaction effect to the flow structure, and the variation of aeroheating in slip flow regime. The results indicate the criterion is not appropriate to adopt in the silp fow regime, which is consistent rational in the continuum regime. In this paper it is improved according to the characteristic of slip flow regime. Numerical simulation indicates that when the flow transfers from the continuum regime to the slip flow regime, the shock wave gets thicker, change rate of the field variables decreases and the peak heating decreases.