TY - GEN
T1 - The reynolds number effect on receptivity to a localized disturbance in a hypersonic boundary layer
AU - Sivasubramanian, Jayahar
AU - Tumin, Anatoli
AU - Fasel, Hermann F.
N1 - Funding Information: This work was supported by AFOSR Grant FA9550-15-1-0265 monitored by Dr. R. Ponnappan. Computer time was provided by the US Army Engineering Research and Development Center (ERDC) under the Department of Defense (DOD) High Performance Computing Modernization Program (HPCMP) challenge project AFOSR26292C4R. 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 Air Force Office of Scientific Research or the U. S. Government. Publisher Copyright: © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - Direct Numerical Simulations of wave packets in hypersonic flat–plate boundary layer reveal that the structure of a wave packet generated by a localized pulse disturbance introduced through a small hole in the wall depends on the location of the disturbance source. The wave packet develops both two–dimensional and three–dimensional structures when the disturbance source is located closer to the leading edge, whereas it has predominantly a two–dimensional nature when the disturbance source is located farther downstream (the Reynolds number effect). Theoretical analysis of the boundary–layer receptivity explains the Reynolds number effect by the different sensitivity of the flow to the first and the second discrete modes at the different disturbance source locations.
AB - Direct Numerical Simulations of wave packets in hypersonic flat–plate boundary layer reveal that the structure of a wave packet generated by a localized pulse disturbance introduced through a small hole in the wall depends on the location of the disturbance source. The wave packet develops both two–dimensional and three–dimensional structures when the disturbance source is located closer to the leading edge, whereas it has predominantly a two–dimensional nature when the disturbance source is located farther downstream (the Reynolds number effect). Theoretical analysis of the boundary–layer receptivity explains the Reynolds number effect by the different sensitivity of the flow to the first and the second discrete modes at the different disturbance source locations.
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U2 - 10.2514/6.2016-4246
DO - 10.2514/6.2016-4246
M3 - Conference contribution
SN - 9781624104329
T3 - 8th AIAA Flow Control Conference
BT - 8th AIAA Flow Control Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 8th AIAA Flow Control Conference, 2016
Y2 - 13 June 2016 through 17 June 2016
ER -