Viscous computations of cold air/air flow around scramjet nozzle afterbody, Volume 4406
Oktay Baysal, Walter C. Englelund, Langley Research Center, Old Dominion University. Dept. of Mechanical Engineering and Mechanics
National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991 - Technology & Engineering - 65 pages
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afterbody flow afterbody flowfield afterbody surface AIAA Paper aircraft analysis approximately Argon Baldwin-Lomax model Baysal boundary conditions boundary layer boundary layer profiles calculations cells centered expansions computational domain computational fluid dynamics computational results conserved variables conventional wind tunnel cowl surface cowl tip curvilinear coordinates density differencing dimensional eddy viscosity experimental data external flow external freestream finer level fixed grid flow adapted grid flow separation freestream flow gases governing equations grid points grid solution hypersonic implicit inviscid iterations Langley Research Center large gradients llllllllll Mach contours Mach number method multigridding NASA Navier-Stokes equations nondimensional nozzle exit plane nozzle-afterbody flows nozzle-afterbody section obtained overexpanded parameters propulsion ramp surface residual Reynolds number Reynolds stresses scheme Scramjet Nozzle scramjet nozzle-afterbody shock shown in Fig simulant gas solver specific-heat-ratio supersonic surface pressure symmetry plane three-dimensional torsion spring turbulence model underexpanded upper cowl upstream upwind velocity viscous wall