We completed all 3 phases of the project. The first phase (Mach 2.3 study) was published in Phys. Rev. Fluids in 2018. The second phase (helping DLR design their Mach 7.4 experiment) was completed primarily during the second year and presented at the 2019 AIAA Scitech meeting. This experiment will now be conducted at DLR during 2020. The final phase of this project was to extend the DNS study to the hypersonic regime in order to understand how the effect of wall-cooling changes with Mach number. This was done by performing DNS of an existing Mach 5.0 experiment from DLR, which confirmed some findings from the Mach 2.3 study but also showed significant differences in the scaling of the interaction length. These findings are currently under review for the Phys. Rev. Fluids journal.
Effects of Strong Wall Cooling on Supersonic and Hypersonic Shock/Boundary-Layer Interactions
2019
18 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Boundary layer , Reynolds number , Skin friction , Mach number , Heat flux , Pressure distribution , Shock waves , Channel flow , Heat transfer , Turbulent mixing , Fluid mechanics , Turbulent boundary layer , Fluid dynamics , Hydrodynamics , Van driest transformation , Wall cooling shock boundary layer , Hypersonic shock boundary layer interactions , Hypersonics
Supersonic and Hypersonic Shock-Boundary-Layer Interaction Database
Online Contents | 1994
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