Hypersonic surface heating computation on blunt bodies
- Paper number
IAC-11,C2,7,21,x9931
- Author
Dr. Guo-hao DING, National University of Defense Technology, China
- Year
2011
- Abstract
Considering the severe aerodynamic heating in hypersonic flows, almost all of the hypersonic vehicles adopt a blunt leading edge to reduce the density of heat flux. Then the accurate prediction of surface heating becomes a key issue in hypersonic flow simulations, but it is still challenging since the numerical schemes for hypersonic flow computation require robustness, accuracy and efficiency. In this paper, the numerical simulation of 3D steady laminar hypersonic flow was considered. The Navior-Stokes equations were employed. The cell centered finite volume based on structured grid was applied for spatial discretization. AUSMPW+ scheme was used for inviscid fluxes, and MUSCL was used for higher order spatial accuracy. Central difference scheme was used to approximate the viscous terms. LU-SGS (Lower-Upper Symmetric Gauss-Seidel) implicit time integration scheme was applied to compute steady flows. Three test cases of different blunt body shapes were studied: hypersonic flow over cylinder, sphere and double-ellipsoid, which are the typical geometries of leading edge in hypersonic vehicle design. Finally the accuracy of the computed surface heating was validated in comparison with the analytical or experimental data, and the complex structure of the computed flowfield was then analyzed in detail. These test results revealed that the AUSMPW+ scheme has the properties of identifying discontinuities, reducing the numerical dissipation and resolving boundary-layer, and it is free of carbuncle phenomena, so it is appropriate to obtain accurate aerodynamic heating on the surface in hypersonic flows.
- Abstract document
- Manuscript document
IAC-11,C2,7,21,x9931.pdf (🔒 authorized access only).
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