An effective flux scheme for hypersonic heating prediction of re-entry vehicles. (English) Zbl 1410.76265
Summary: In this article, an effective computational method called TVM is proposed for the hypersonic heating prediction of the re-entry vehicles. Aiming at resolving the boundary layer accurately, the method adopts the splitting manner of the Toro and Vazquez’s splitting procedure with an improved low-dissipation modification. Also, the method is robust against the shock anomaly in hypersonic flows. The detailed construction of the scheme is presented, and a series of testcases are conducted to validate the performance of the newly developed scheme. Finally, the scheme is applied to the simulation of the hypersonic re-entry vehicles. Numerical results show its high performance in the prediction of the re-entry vehicles hypersonic heating load compared to traditional methods.
MSC:
| 76M12 | Finite volume methods applied to problems in fluid mechanics |
| 65M08 | Finite volume methods for initial value and initial-boundary value problems involving PDEs |
| 76K05 | Hypersonic flows |
| 76Nxx | Compressible fluids and gas dynamics |
Keywords:
computational fluid dynamics; hypersonic aeroheating prediction; all speeds; re-entry vehicles; Navier-Stokes equationsReferences:
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