Direct numerical simulation of supersonic turbulent flow in an expansion-compression corner at mach=2.9
(2014)
Presentation / Conference Contribution
Shock-wave/turbulent boundary layer interactions (SWTBLI) are prevalent phenomena in high-speed flights, which could cause large flow separation and high wall heat flux and strong pressure fluctuation, therefore, affect significantly the aero-thermod... Read More about Direct numerical simulation of supersonic turbulent flow in an expansion-compression corner at mach=2.9.