TY - GEN
T1 - Slip effects on the stability of supersonic laminar flat plate boundary layer
AU - Klothakis, Angelos
AU - Quintanilha, Helio
AU - Sawant, Saurabh S.
AU - Theofilis, Vassilis
AU - Levin, Deborah A.
N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Current worldwide efforts to develop maneuverable vehicles flying in rarefied gas hypersonic environments require quantification of laminar-turbulent transition in the hypersonic boundary layers formed on lifting surfaces and control fins. The present contribution commences efforts to document the effect of wall-slip velocity and temperature distributions on the linear stability of hypersonic laminar boundary layers developing on a semi-infinite flat plate, for Knudsen numbers kn ∼ O(0.05), corresponding to flight altitudes of 35km ≤ ℎ ≤ 65km and, at first instance, low Reynolds numbers, Re∼ O(103 − 104 ). The steady laminar base flow is obtained using the Direct Simulation Monte Carlo (DSMC) method. Results on the mean-free-path and wall-normal velocity and temperature gradients obtained are used to construct slip-velocity and temperature-jump boundary conditions along the plate surface, following recent updates of the Maxwell / von Smoluchowski theory. Linear stability analysis of the DSMC profiles extracted from the simulation and those obtained by the updated compressible boundary layer theory reveals quantitative but not qualitative differences on the characteristics of the leading flow eigenmodes over the range of parameters examined. Work is underway to characterise whether the observed differences are a result of a residual pressure gradient present in the DSMC simulation, or intrinsic to kinetic fluctuations unaccounted for in the framework of Navier-Stokes/boundary layer theory.
AB - Current worldwide efforts to develop maneuverable vehicles flying in rarefied gas hypersonic environments require quantification of laminar-turbulent transition in the hypersonic boundary layers formed on lifting surfaces and control fins. The present contribution commences efforts to document the effect of wall-slip velocity and temperature distributions on the linear stability of hypersonic laminar boundary layers developing on a semi-infinite flat plate, for Knudsen numbers kn ∼ O(0.05), corresponding to flight altitudes of 35km ≤ ℎ ≤ 65km and, at first instance, low Reynolds numbers, Re∼ O(103 − 104 ). The steady laminar base flow is obtained using the Direct Simulation Monte Carlo (DSMC) method. Results on the mean-free-path and wall-normal velocity and temperature gradients obtained are used to construct slip-velocity and temperature-jump boundary conditions along the plate surface, following recent updates of the Maxwell / von Smoluchowski theory. Linear stability analysis of the DSMC profiles extracted from the simulation and those obtained by the updated compressible boundary layer theory reveals quantitative but not qualitative differences on the characteristics of the leading flow eigenmodes over the range of parameters examined. Work is underway to characterise whether the observed differences are a result of a residual pressure gradient present in the DSMC simulation, or intrinsic to kinetic fluctuations unaccounted for in the framework of Navier-Stokes/boundary layer theory.
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M3 - Conference contribution
AN - SCOPUS:85100124486
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 28
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -