Trajectory-based Coupled Analysis of Viscous Shock Layer and Charring Material Ablation at Stagnation Point

鈴木, 宏二郎, Suzuki, Kojiro

To predict the characteristics of the ablation thermal protection for the MUSEE-C superorbital re-entry capsule, the trajectory-based analysis of the hypersonic shock layer flow and the ablator interior has been made on the stagnation line in a coupled manner. For the flow analysis, the Viscous Shock-Layer (VSL) equations with the nonequilibrium chemistry of C-O-H-N 26 species are solved. For the ablator, the in-depth thermal response is solved by the Charring Material Ablation (CMA) model. The boundary condition at the surface, which is necessary for both solutions, is determined by the mass and energy balance. Various surface reactions and the surface injection of the pyrolysis gas are considered. The results are compared with the experimental data obtained at the arc-heated wind tunnel. Analysis by using the empirical relations all along the re-entry trajectory is also made and the results are compared with those by the VSL/CMA coupled method. It is shown that such engineering prediction method provides reasonable prediction for the surface temperature and the mass loss of the ablator with sufficient safety margin. The effects of the initial ablator thickness on the ablator temperature are also discussed.

資料番号: SA0200026000

Trajectory-based Coupled Analysis of Viscous Shock Layer and Charring Material Ablation at Stagnation Point

Search this article

Abstract

Journal

Details 詳細情報について

Export

Report a problem

Trajectory-based Coupled Analysis of Viscous Shock Layer and Charring Material Ablation at Stagnation Point

Search this article

Abstract

Journal

Details 詳細情報について

Export

Report a problem

Project list