TY - GEN
T1 - Shock wave boundary layer interaction in a hypersonic laminar flow on a hollow cylinder flare
AU - Mortazavi, Mahsa
AU - Knight, Doyle
N1 - Funding Information: This work was supported by the Offfice of Naval Research, ONR under Grant N00014-14-1-0827 (Gil Graff, Program Manager). The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the offficial policies or endorsements, either expressed or implied, of the Offfice of Naval Research, or U.S. government. Publisher Copyright: © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.
PY - 2016
Y1 - 2016
N2 - Shock wave boundary layer interaction over an axisymmetric hollow cylinder flare creates a complex flow structure due to the adverse pressure gradient imposed on the boundary layer and the formation of the multilayer shock wave structure. This phenomenon can be critical due to its unsteady nature and the low frequency load it applies on the vehicle at hypersonic speeds. Understanding this phenomena and finding techniques to control it is very important for flights at high Mach numbers. The prediction of the heat transfer on the vehicle in hypersonic speeds with shock wave boundary layer interaction can be very complicated. The capability of numerical models to predict the pressure and heat transfer on the vehicle with shock wave boundary layer interaction is up to debate. This research deals with the assessment of the laminar perfect gas model to predict the pressure and heat transfer on a hollow cylinder flare in a flow at Mach 10. The numerical results are compared with experimental data for validation.
AB - Shock wave boundary layer interaction over an axisymmetric hollow cylinder flare creates a complex flow structure due to the adverse pressure gradient imposed on the boundary layer and the formation of the multilayer shock wave structure. This phenomenon can be critical due to its unsteady nature and the low frequency load it applies on the vehicle at hypersonic speeds. Understanding this phenomena and finding techniques to control it is very important for flights at high Mach numbers. The prediction of the heat transfer on the vehicle in hypersonic speeds with shock wave boundary layer interaction can be very complicated. The capability of numerical models to predict the pressure and heat transfer on the vehicle with shock wave boundary layer interaction is up to debate. This research deals with the assessment of the laminar perfect gas model to predict the pressure and heat transfer on a hollow cylinder flare in a flow at Mach 10. The numerical results are compared with experimental data for validation.
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U2 - https://doi.org/10.2514/6.2016-0351
DO - https://doi.org/10.2514/6.2016-0351
M3 - Conference contribution
SN - 9781624103933
T3 - 54th AIAA Aerospace Sciences Meeting
BT - 54th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA Aerospace Sciences Meeting, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -