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 language||English (US)|
|Title of host publication||46th AIAA Fluid Dynamics Conference|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2016|
|Event||46th AIAA Fluid Dynamics Conference, 2016 - Washington, United States|
Duration: Jun 13 2016 → Jun 17 2016
|Name||46th AIAA Fluid Dynamics Conference|
|Other||46th AIAA Fluid Dynamics Conference, 2016|
|Period||6/13/16 → 6/17/16|
Bibliographical noteFunding Information:
The authors gratefully acknowledge the Office of Naval Research Grant Number N00014-15-1-2522 for the support of this research.
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Copyright 2016 Elsevier B.V., All rights reserved.