Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 5
... present mission plans call for entry off the equatorial plane so as to avoid the most intense portion of the ionization belts . Therefore , the present calculations include a trajectory inclined 17.5 deg to the equator . The probe ...
... present mission plans call for entry off the equatorial plane so as to avoid the most intense portion of the ionization belts . Therefore , the present calculations include a trajectory inclined 17.5 deg to the equator . The probe ...
Page 19
... present results for the revised model atmospheres also showed the following : 1 ) The radiative heating values for off - equatorial entries , inclined 17.5 deg to the equator , are never more than 20 % greater than for equatorial ...
... present results for the revised model atmospheres also showed the following : 1 ) The radiative heating values for off - equatorial entries , inclined 17.5 deg to the equator , are never more than 20 % greater than for equatorial ...
Page 157
... present radiative heating rates compare well with the detailed calculations and are within 10 % for this case . The convective heating rates with radiation are , again , about 15 % to 20 % lower than those of Ref . 14. The present ...
... present radiative heating rates compare well with the detailed calculations and are within 10 % for this case . The convective heating rates with radiation are , again , about 15 % to 20 % lower than those of Ref . 14. The present ...
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/mē 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