Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 103
... shock layer dramatically . The change in tempera- ture , however , is significant , and ( as would be expected ) the maximum change occurs just behind the shock . There is a slight change in the pressure near the body but virtually no ...
... shock layer dramatically . The change in tempera- ture , however , is significant , and ( as would be expected ) the maximum change occurs just behind the shock . There is a slight change in the pressure near the body but virtually no ...
Page 167
... shock wave = wall condition S sh W = 15530 NO 8 stagnation - point conditions = derivative with respect to = transverse direction = dimensional freestream conditions Superscripts ... shock - layer 3 - D VISCOUS SHOCK - LAYER FLOWS 167.
... shock wave = wall condition S sh W = 15530 NO 8 stagnation - point conditions = derivative with respect to = transverse direction = dimensional freestream conditions Superscripts ... shock - layer 3 - D VISCOUS SHOCK - LAYER FLOWS 167.
Page 303
... shock layer . The para- meters involved in these calculations represent the details of the shock layer , i.e. , temperature , pressure , standoff , composition , and radiation cross sections . The nominal condi- tions are those of case ...
... shock layer . The para- meters involved in these calculations represent the details of the shock layer , i.e. , temperature , pressure , standoff , composition , and radiation cross sections . The nominal condi- tions are those of case ...
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