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Sidewall Effects on Exact Reynolds-Stress Budgets in an Impinging Shock Wave/Boundary Layer InteractionLarge-eddy simulations are performed using wall-resolved mesh for a Mach 2.29 impinging shock wave/boundary-layer interaction. Flow conditions are based on an experiment and therefore entire span was simulated, including the two sidewalls. Mean flow comparison with the experimental data showed that the interaction was larger in the simulation. Time-series analysis of a rake of pressure probes immediately downstream of the mean reflected shock position showed a peak in weighted power spectral density occurred about $St_{Lint}=0.01$, owing to a larger interaction length. Budgets of Reynolds-stress transport calculated across the span and along the corner bisector showed high degree of anisotropy. Merging of the secondary flows and separation along the corner gives rise to unstablecounter rotating vortices, which straddle the corner and grow in size. This also leads to a development of new behavior in the viscous sublayer along the corner bisector, where the pressure strain andmolecular diffusion mechanisms become prominent.
Document ID
Document Type
Technical Memorandum (TM)
Vyas, Manan A.
(NASA Glenn Research Center Cleveland, OH, United States)
Yoder, Dennis A.
(NASA Glenn Research Center Cleveland, OH, United States)
Gaitonde, Datta
(Ohio State Univ. Columbus, OH, United States)
Date Acquired
June 5, 2019
Publication Date
March 1, 2019
Subject Category
Aeronautics (General)
Report/Patent Number
Funding Number(s)
WBS: 109492.
Distribution Limits
Public Use Permitted.
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