Direct numerical simulation is performed on a 38.1% scale HIFiRE-5 forebody to study stationary crossflow instability. Computations use the US3D Navier-Stokes solver to simulate Mach 6 flow at Reynolds numbers of 8.1×106/m and 11.8×106/m, which are conditions used by quiet tunnel experiments at Purdue University. Distributed roughness with point-to-point height variation on the computational grid and maximum heights of 0.5-4.0 µm is used with the intent to emulate smooth-body transition and excite the naturally-occuring most unstable disturbance wavenumber. Disturbance growth rates and wavelength evolution are analyzed, and the effect of roughness height and forcing character is considered. A steady physical mechanism for the sharp increase in wall heat flux seen in both computations and experiment is introduced. Crossflow vortex coalescence is observed and a possible cause is discussed.
|Original language||English (US)|
|Title of host publication||54th AIAA Aerospace Sciences Meeting|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2016|
|Event||54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States|
Duration: Jan 4 2016 → Jan 8 2016
|Name||54th AIAA Aerospace Sciences Meeting|
|Other||54th AIAA Aerospace Sciences Meeting, 2016|
|Period||1/4/16 → 1/8/16|
Bibliographical noteFunding Information:
This work was sponsored by the Air Force Office of Scientific Research under grant FA9550-12-1-0064. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the funding agencies or the U.S. Government.
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.