Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 335
... configuration with the highest drag coefficient , since initial probe mass and base area are held constant . In fact , for the most slender body considered ( 30 - deg sphere - cone configuration ) , peak heating occurs at a stagnation ...
... configuration with the highest drag coefficient , since initial probe mass and base area are held constant . In fact , for the most slender body considered ( 30 - deg sphere - cone configuration ) , peak heating occurs at a stagnation ...
Page 337
... configuration . large incremental surface area , reducing the ablation rate there significantly reduces the total mass loss . The optimized initial configuration before entry into the Jovian atmosphere and the heat - shield final shape ...
... configuration . large incremental surface area , reducing the ablation rate there significantly reduces the total mass loss . The optimized initial configuration before entry into the Jovian atmosphere and the heat - shield final shape ...
Page 338
... configuration . wind - tunnel tests with simulated surface blowing are required to define the flowfield and aerodynamics for the optimized shape . A closer examination of the heating rates for the opti- mized configuration is presented ...
... configuration . wind - tunnel tests with simulated surface blowing are required to define the flowfield and aerodynamics for the optimized shape . A closer examination of the heating rates for the opti- mized configuration is presented ...
Contents
Effects of Atmospheric Structure on Radiative Heating | 3 |
Radiative Flux Penetration through a Blown Shock Layer | 22 |
Approximate Inviscid Radiating Flowfield Analysis | 42 |
Copyright | |
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Common terms and phrases
ablation absorption coefficient AIAA AIAA Journal AIAA Paper altitudes analysis angle of attack base blockage body surface boundary layer bow shock calculations carbon phenolic chemical chemical equilibrium computed configuration correlation distribution energy enthalpy entry conditions equilibrium experimental flow flowfield freestream graphite H₂ heat shield Heat Transfer heat-transfer hydrogen hyperboloid inertial entry angle intensity inviscid Jupiter Jupiter entry km/sec laminar laser mass loss mass transfer material mixture model atmospheres MW/m² NASA nominal nondimensional nonequilibrium number density obtained Outer Planet Entry parameters PRECURSOR EFFECT precursor heating precursor region predicted present pressure radiation radiative and convective radiative flux radiative heat flux radiative heating rates recession Reynolds number shock-layer shown in Fig silica solution species spectral spectral flux sphere-cone stagnation point stagnation-point temperature thermal thermochemical thermodynamic tion trajectory turbulent uncertainty variation velocity viscous shock-layer VSL3D wall