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

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.

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Document Details

Document Type
Technical Report
Publication Date
Dec 06, 2019
Accession Number
AD1104806

Entities

People

  • Johan Larsson
  • Tamer A. Zaki

Organizations

  • University of Maryland

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Boundary Layer
  • Channel Flow
  • Coefficients
  • Compression Waves
  • Experimental Data
  • Heat Transfer
  • Layers
  • Mach Number
  • Mechanical Engineering
  • Pressure Distribution
  • Reynolds Number
  • Simulations
  • Skin Friction
  • Three Dimensional
  • Turbulent Flow
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Technical Research and Report Writing.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow