Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 7
... Trajectory Calculations The entry trajectories were calculated for a three - degree- of - freedom trajectory using the computer program known as POST.14 For the previous model atmospheres , the trajectories were initialized at an ...
... Trajectory Calculations The entry trajectories were calculated for a three - degree- of - freedom trajectory using the computer program known as POST.14 For the previous model atmospheres , the trajectories were initialized at an ...
Page 27
... trajectory calculation is initiated ( zero time ) at an altitude of 450 km . Condition II is the trajectory for a 50 - deg spherically blunted cone entering an atmosphere consisting of 89 % H2 and 11 % He by volume . The Jupiter Orbiter ...
... trajectory calculation is initiated ( zero time ) at an altitude of 450 km . Condition II is the trajectory for a 50 - deg spherically blunted cone entering an atmosphere consisting of 89 % H2 and 11 % He by volume . The Jupiter Orbiter ...
Page 324
... trajectory modification due to changing vehicle mass is allowed . Trajectory Calculations The probe entry trajectories are computed using an exact two - degree - of - freedom , spherical planet analysis . The fourth- order Runga - Kutta ...
... trajectory modification due to changing vehicle mass is allowed . Trajectory Calculations The probe entry trajectories are computed using an exact two - degree - of - freedom , spherical planet analysis . The fourth- order Runga - Kutta ...
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