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NTIS 바로가기International journal of heat and mass transfer, v.70, 2014년, pp.81 - 90
John, B. , Kulkarni, V.N. , Natarajan, G.
Shock-wave boundary layer interaction (SWBLI) and associated changes in wall properties for ramp induced flow breakdown have been considered in the present studies. A two dimensional finite volume based CFD solver has been developed and implemented successfully to study the SWBLI. Pressure measureme...
Prog. Aerosp. Sci. Schneider 40 1-2 1 2004 10.1016/j.paerosci.2003.11.001 Hypersonic laminar-turbulent transition on circular cones and scramjet forebodies
Anderson 1989 Hypersonic and High Temperature Gas Dynamics
D.R. Chapman, D.M. Kuehn, H.K. Larson, Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition, NACA TN 3869, NACA Rep. 1356, 1957.
J.R. Sterrett, J.C. Mery, Experimental separation studies for two-dimensional wedges and curved surfaces at M=4.8 to 6.2, NASA TN D-1014, 1962.
Coet 1992 Shock-Wave Boundary Layer Interaction with Entropy Layer Effect in Hypersonic Flow
AIAA J. Myers 51 10 2410 2013 10.2514/1.J052313 Using ultrasound and the extended kalman filter for characterizing aerothermodynamic environments
Int. J. Heat Mass Transfer Myers 55 9-10 2472 2012 10.1016/j.ijheatmasstransfer.2012.01.012 High heat flux point source sensitivity and localization analysis for an ultrasonic sensor array
D.A. Needham, J.L. Stollery, Boundary-layer separation in hypersonic flow, in: AIAA paper 66-455, 1996.
Comput. Fluids Grasso 25 6 561 1996 10.1016/0045-7930(96)00019-9 Analysis of hypersonic shock wave laminar boundary-layer interaction phenomena
AIAA J. Holden 8 l 2179 1970 10.2514/3.6084 Boundary-layer displacement and leading-edge bluntness effects on attached and separated laminar boundary layers in a compression corner. Part I: Theoretical study
AIAA J. Holden 9 l 84 1971 10.2514/3.6127 Boundary-layer displacement and leading-edge bluntness effects on attached and separated laminar boundary layers in a compression corner. Part II: Experimental study
Phys. Fluids Davis 12 10 2661 2000 10.1063/1.1289553 Separation length in high-enthalpy shock/boundary-layer interaction
Int. J. Comput. Fluid Dyn. Layland 6 1 71 1996 10.1080/10618569608940775 Shock-wave/boundary layer interaction at hypersonic speed by an implicit Navier-Stokes solver
Aerosp. Sci. Technol. Marini 5 257 2001 10.1016/S1270-9638(01)01109-9 Analysis of hypersonic compression ramp laminar flows under sharp leading edge conditions
10.1504/PCFD.2014.060142 B. John, G. Sarath, V. Kulkarni, G. Natarajan, Performance comparison of flux schemes for numerical simulation of high-speed inviscid flows, Prog. Comput. Fluid Dyn. Int. J. (2013) (in press).
Philos. Mag. S. Sutherland 5 36 507 1893 10.1080/14786449308620508 The viscosity of gases and molecular force
J. Comput. Phys. Liou 107 1 23 1993 10.1006/jcph.1993.1122 A new flux splitting scheme, NASA TM-104404 1991
Blazek 2001 Computational Fluid Dynamics: Principles and Applications
J. Comput. Phys. Venkatakrishnan 118 1 120 1995 10.1006/jcph.1995.1084 Convergence to steady-state solutions of the euler equations on unstructured grids with limiters
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