Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 7
... inertial entry angles of -5 , -7.5 , and -10 deg . All trajectories were calculated for entry along the equatorial plane . These entry parameters usually are associated with previous calculations for Jupiter entry . For the revised ...
... inertial entry angles of -5 , -7.5 , and -10 deg . All trajectories were calculated for entry along the equatorial plane . These entry parameters usually are associated with previous calculations for Jupiter entry . For the revised ...
Page 8
... Entry altitude , km 450 1000 Inertial entry velocity , km / s 60 60 Inertial entry angle at entry altitude , deg -5 , -7.5 , -10 -7 , -9 , -11 Inertial entry angle at 450 km alt Inertial azimuth angle , deg Latitude , deg -5 , -7.5 ...
... Entry altitude , km 450 1000 Inertial entry velocity , km / s 60 60 Inertial entry angle at entry altitude , deg -5 , -7.5 , -10 -7 , -9 , -11 Inertial entry angle at 450 km alt Inertial azimuth angle , deg Latitude , deg -5 , -7.5 ...
Page 18
... inertial entry angle in Figs . 14 and 15. The total radiative heating can range from 970 to 3800 MJ , a factor of 4 , for the probe configuration considered in the present study . Concluding Remarks New estimates of the radiative ...
... inertial entry angle in Figs . 14 and 15. The total radiative heating can range from 970 to 3800 MJ , a factor of 4 , for the probe configuration considered in the present study . Concluding Remarks New estimates of the radiative ...
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