Hypersonic Technology for Military Application (1989) / Chapter Skim
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Appendix E: Request for Information from NASP Contractors
Appendix E: Request for Information from NASP Contractors
Pages 92-99
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PIO pilot induced oscillations PNS parabolized Reynolds-averaged Navier-Stokes equations psf pounds per square foot RST rapidly solidified titanium TOGW take-off gross weight TPS thermal protection system ZAP zone anneal-processed
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Boundary layer can be laminar or, downstream of transition point, turbulent. cold wall The condition of low model surface temperatures to allow more accurate aerodynamic testing in a hypersonic wind tunnel.
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Knudsen number, Kn Mean free path divided by characteristic length of body. laminar boundary layer Comprise successive laminar layers, that adjacent to surface having zero relative velocity and successive layers adding velocity out to the free stream.
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Hence ram inlet, ram pressure, ramjet, ram air, ram effect. ramjet Air-breathing jet engine similar to turbojet but without mechanical compressor or turbine; compression is accomplished entirely by ram and is thus sensitive to vehicle forward speed and non-existent at rest (hence ram cannot start from rest)
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sloshing Gross oscillatory motion of liquid in tank sufficient to impose severe structural stress or affect vehicle trajectory. stagnation point Point on surface of body in viscous fluid flow (one facing upstream and one down)
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HYPERSONIC TECHNOLOGY FOR MILITARY APPLICATION APPENDIX D: Dimensionless Groups in Fluid Mechanics Qualitative ratio Parameter Definition of effects Importance Reynolds number Re = pUL/p Inertia/Viscosity Always 73 Mach number Ma= U/a Flow speed/Sound speed Compressible flow Froude number Fr= U2/gL Inertia/Gravity Free-surface flow Weber number We = pU2L/T Inertia/Surface tension Free-surface flow Cavitation number Ca= p-pU/pU2 Pressure/Inertia Cavitation (Euler number) Prandtl number Pr = pcp/k Dissipation/Conduction Heat convection Eckert number Ec = U2/cpTo Kinetic energy/Enthalpy Dissipation Specific-heat ratio 7= cp/c',, Enthalpy/Internal energy Compressible flow Strouhal number St = wL/U Oscillation/Mean speed Oscillating flow Roughness ratio c/L Wall roughness/ Turbulent, rough walls Body length Grashof number Gr = ,B~TgL3p2/~2 Buoyancy/Viscosity Natural convection Temperature ratio TOO/To Wall temperature/ Heat transfer Stream temperature Pressure coefficient Cp = p_poO/IpU2 Static pressure/ Dynamic pressure Aerodynamics, hydrodynamics
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( 1 /PR) 2/3 Qualitative ratio of effects Lift force/ Dynamic force Drag force/ Dynamic force Mass diffusion/ Energy diffusion Measure of continuum or Free molecular flow Reynolds analogy between friction and heat transfer Viscous to Diffusion ratio The only unusual parameter here is lo, which is a diffusion coefficient.
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the level of technical risk in a single-stage to orbit research vehicle, and strategies for risk reduction. by the research vehicle program approach to maximize the acquisition of knowledge in the most critical technical areas.
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