Abstract: The laminar N-S equations are solved for hypersonic flow over capsule-typere-entry vehicles by using the second-order windward TVD scheme. The detail flow-field structures and pressure distribution along body, surface are given, and its good agreement with experiment and reference is reached. The calcultions also show that the variation of raddius R2 dose not cause much flowfield change on the afterbody, but it has a great effect on the heating rate near the shoulder. In the case of R2 = 0.2, heating rate peak on the shoulder is slightly less than the stagnation values; however, when R2is, equal to 0.05, this peak is much higher and exceeds the stagnation value by 30%.

Key words: hypersonic flow, numerical simulation. TVD scheme