Investigation of supersonic/hypersonic shock-wave/boundary-layer interactions (SBLIs)
Numerical simulations of supersonic/hypersonic laminar shock-wave/boundary-layer interactions (SBLIs) have been carried out by solving the Navier-Stokes (NS) equations using a compressible flow code over a wide range of Mach number, Reynolds number and shock strength. The results were analysed by means of correlation laws, simplified theoretical analysis, and comparison with experiments. The analysis confirmed that the flow properties in the vicinity of the separation point conformed to the free interaction concept, in agreement with other investigators. The correlation of separation length, which included the viscous interaction parameter, \( \bar \chi \), revealed different constants obtained at supersonic and hypersonic speed. The comparisons showed that the experimental results exhibited a higher heating rate than predicted by laminar SBLI simulations, possibly caused by free shear layers transition.
KeywordsReynolds Number Mach Number Incident Shock Separation Point Separation Bubble
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