Abstract:
Hypersonic aerodynamic heating characteristics for an aerospace vehicle at
Ma=8.0 and
Ma=10.2 was calculated by computational fluid dynamics (CFD) method and engineering rapid computational method based on in-viscid surface streamlines. The Roe flux difference scheme(FDS) was employed in the CFD method. For the engineering rapid computational method, the in-viscid surface streamlines were determined by the Euler equations on the Cartesian grid, and the surface heating distribution can be computed by the integration along the in-viscid surface streamlines according to the Eckert reference enthalpy theory. Both laminar and turbulent flows were simulated in the present study. Comparisons were carried out between the engineering rapid computational results, the CFD results, and the experimental results. The results show that the heating distribution can be well predicated for the airframe and the wing of the aerospace vehicle by the CFD method and the rapid engineering method developed in this paper. The error of the aerodynamic heating distribution at the stagnation point is less than 5%.