Accession Number:

AD1104806

Title:

The Effects of Strong Wall Cooling on Supersonic and Hypersonic Shock/Boundary-Layer Interactions

Descriptive Note:

Technical Report,15 Sep 2016,31 Aug 2019

Corporate Author:

Maryland Univ College Park College Park United States

Personal Author(s):

Report Date:

2019-12-06

Pagination or Media Count:

18.0

Abstract:

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.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE