Abstract: Abstract The work in this paper is based on the optimization software, using the exactly optimization technique. The hypersonic aerodynamic performance is calculated by numerically solving the Euler equations and the maximum surface heat flux is calculated by solving the FayRiddell equation. To test our method, the CTV is optimized. The Spaceship reentry capsule has been optimized as a particular instance. This research work can be as the groundwork for the reentry capsule optimization.