Preliminary investigation of momentum diffusion between two supersonic airstreams in the presence of shock waves, Volume 4974
John P. Weidner, Carl A. Trexler, United States. National Aeronautics and Space Administration, Langley Research Center
National Aeronautics and Space Administration, 1969 - Technology & Engineering - 77 pages
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ahead of model ahead of shock APPENDIX A TABULATION base plate boundary-layer calculations centimeters combustion computer program constant static pressure correlate the data dashed curves DATA THROUGH MIXING eddy-viscosity constant eddy-viscosity model effective shock waves expansion wave experimental data extra shock Figure 11 flow field given in figure increase in eddy increasing eddy viscosity injection nozzle input inviscid isentropic Langley Research Center Mach number mixing data mixing rate mixing region mixing width mixing zone MOMENTUM DIFFUSION near-region mixing newtons/centimeter2 oblique shock obtained parameter pitot pitot-pressure survey primary air primary and secondary primary-air stream pt 2/Pt Pt.calc ramjet rate of mixing S-axis Schlieren secondary air secondary free-stream velocities secondary streams shock region stagnation pressure station of x/d survey station TABULATION OF DATA Theoretical Mixing theoretical solution based theoretical velocity profiles top surface total pressure total temperature tunnel flow primary TWO-WAVE SHOCK SYSTEM U.S. Air Force velocity profiles computed