TY - GEN
T1 - Effects of reynolds number on laminar boundary layer shock-interaction hypersonic flows on a double cone
AU - Tumuklu, Ozgur
AU - Levin, Deborah A.
AU - Theofilis, Vassilis
N1 - Funding Information:
The research of O.T. and D.A.L. is being supported by the Air Force Office of Scientific Research through AFOSR Grant No. FA9550-11-1-0129 with a subcontract Award No. 2010-06171-01 to UIUC. O.T. and D.A.L. are also grateful for the computational resource provided on ERDC Topaz and Onyx, AFRL Thunder and Centennial. The work of V.T. is sponsored by the Air Force Office of Scientific Research, Air Force Material Command, USAF, under Grant No. FA9550-15-1-0387 Global transient growth mechanisms in high-speed flows with application to the elliptic cone, and Grant No. FA9550-17-1-0115 Global Modal and Non-Modal Instability Analyses of Shock-Induced Separation Bubbles, with V.T. as Principal Investigator and Dr. Ivett Leyva as Program Officer.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - Shock-dominated hypersonic laminar flows over a double cone are investigated using time accurate direct simulation Monte Carlo combined with the residuals algorithm for unit Reynolds numbers gradually increasing from 9.35×104 to 3.74×105 m−1 at Mach numbers changing from about 12 to 16 for nitrogen and reacting air cases. The main flow features, such as the strong bow-shock, location of the separation shock, the triple point, and the entire laminar separated region show a time-dependent behavior. It was observed that the effects of Reynolds number on the structure and extent of the separation region are profound. As the Reynolds number is increased for the LENS-I cases, larger pressure values in the under-expanded jet region due to strong shock interactions form more prominent λ-shocklets in the supersonic region between two contact surfaces. The chemical reactions for higher enthalpies reduce the size of the separation region significantly and good agreement was observed between the DSMC predicted surface heating values and pressures and the measurements. The catalytic reactions increase the surface heating. A good agreement was also observed between the recent CFD1 calculations and DSMC.
AB - Shock-dominated hypersonic laminar flows over a double cone are investigated using time accurate direct simulation Monte Carlo combined with the residuals algorithm for unit Reynolds numbers gradually increasing from 9.35×104 to 3.74×105 m−1 at Mach numbers changing from about 12 to 16 for nitrogen and reacting air cases. The main flow features, such as the strong bow-shock, location of the separation shock, the triple point, and the entire laminar separated region show a time-dependent behavior. It was observed that the effects of Reynolds number on the structure and extent of the separation region are profound. As the Reynolds number is increased for the LENS-I cases, larger pressure values in the under-expanded jet region due to strong shock interactions form more prominent λ-shocklets in the supersonic region between two contact surfaces. The chemical reactions for higher enthalpies reduce the size of the separation region significantly and good agreement was observed between the DSMC predicted surface heating values and pressures and the measurements. The catalytic reactions increase the surface heating. A good agreement was also observed between the recent CFD1 calculations and DSMC.
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U2 - 10.2514/6.2018-4032
DO - 10.2514/6.2018-4032
M3 - Conference contribution
AN - SCOPUS:85051298222
SN - 9781624105531
T3 - 2018 Fluid Dynamics Conference
BT - 2018 Fluid Dynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 48th AIAA Fluid Dynamics Conference, 2018
Y2 - 25 June 2018 through 29 June 2018
ER -