Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 315
... tion and absorption coefficient constitute most of the abla- tion layer's contribution to the recession uncertainty . The flight envelope , the inviscid shock layer , and the mechanical erosion are secondary factors with each ...
... tion and absorption coefficient constitute most of the abla- tion layer's contribution to the recession uncertainty . The flight envelope , the inviscid shock layer , and the mechanical erosion are secondary factors with each ...
Page 337
... tion and formation of strong secondary shocks that would in- crease the heat - shield recession rate on the flare . The addi- tion of a flare to a slender body generally increases its stability by moving the center of pressure rearward ...
... tion and formation of strong secondary shocks that would in- crease the heat - shield recession rate on the flare . The addi- tion of a flare to a slender body generally increases its stability by moving the center of pressure rearward ...
Page 338
... tion is that , for the 35 / 60 - deg inflected configuration , no- blowing convective heating rates are a little more than double the no - blowing radiative heating rates . Even when the block- age effects due to the injection of heat ...
... tion is that , for the 35 / 60 - deg inflected configuration , no- blowing convective heating rates are a little more than double the no - blowing radiative heating rates . Even when the block- age effects due to the injection of heat ...
Contents
Effects of Atmospheric Structure on Radiative Heating | 3 |
Radiative Flux Penetration through a Blown Shock Layer | 22 |
Approximate Inviscid Radiating Flowfield Analysis | 42 |
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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