The aerothermodynamic loadings associated with shock wave boundary layer interactions (shock interactions) must be carefully considered in the design of hypersonic air vehicles. The capability of Computational Fluid Dynamics (CFD) software to accurately predict hypersonic shock wave laminar boundary layer interactions is examined. A series of independent computations performed by researchers in the US and Europe are presented for two generic configurations (double cone and cylinder) and compared with experimental data. The results illustrate the current capabilities and limitations of modern CFD methods for these flows.
Bibliographical noteFunding Information:
The research by the first author (DK) is supported by the US Air Force Office of Scientific Research under Grant FA9550-07-1-0228 managed by Dr. John Schmisseur. The assistance of Michael Holden (CUBRC) and Klaus Hannemann (DLR) is gratefully appreciated. Dimitris Drikakis wishes to thank A. Mosedale, S. Tissera and V. Titarev for their support with regard to the numerical simulations. Andrea Lani wishes to thank Dr. Marco Panesi (former collaborator at the VKI), whose role has been fundamental in the implementation of thermal non-equilibrium models used by our flow solvers.
- Computational fluid dynamics
- Shock waves