Trip-induced transition of a mach 5.65 low reynolds number boundary layer

Prakash Shrestha, Graham Candler

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

We present a study of unsteady behavior in a laminar Mach 5.65 boundary layer caused by an array of three diamond shaped trips on a at plate. The purpose of this study is to investigate transition of the tripped boundary layer to turbulence using US3D, a finite volume based compressible Navier-Stokes solver. Direct numerical simulation is conducted of an experimental set-up present in Actively Controlled Expansion Hypersonic Wind Tunnel, Texas A & M University National Aerothermochemistry Laboratory. We perform both 2D and 3D simulations. Planar acoustic disturbance is applied at the inlet of the 2D domain to mimic the wind tunnel ambient environment. We then map 2D spectral contents at 30 mm from the leading edge to the 3D inlet. The array of trips is used in the 3D domain with spanwise periodic boundary conditions. In the 3D domain, we determine optimal modes of the streamwise velocity fluctuations downstream of the trips using Sparsity-Promoting Dynamic Mode Decomposition (SPDMD). For validation of our numerical simulation, we compare mean mass flux obtained from the DNS to that from the experimental test.

Original languageEnglish (US)
Title of host publication46th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104367
StatePublished - 2016
Event46th AIAA Fluid Dynamics Conference, 2016 - Washington, United States
Duration: Jun 13 2016Jun 17 2016

Publication series

Name46th AIAA Fluid Dynamics Conference

Other

Other46th AIAA Fluid Dynamics Conference, 2016
Country/TerritoryUnited States
CityWashington
Period6/13/166/17/16

Bibliographical note

Funding Information:
The authors gratefully acknowledge the Office of Naval Research Grant Number N00014-15-1-2522 for the support of this research.

Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Copyright:
Copyright 2016 Elsevier B.V., All rights reserved.

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