Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 81
... bow shock , n * / R * = pressure , p * / ( p * V * 2 ) ∞ = Prandtl number u * C * / k * = net radiant heat flux , q ... bow shock = coordinate along the bow shock , s * / R * , temperature , T * / T * = = reference temperature , 27,315 ...
... bow shock , n * / R * = pressure , p * / ( p * V * 2 ) ∞ = Prandtl number u * C * / k * = net radiant heat flux , q ... bow shock = coordinate along the bow shock , s * / R * , temperature , T * / T * = = reference temperature , 27,315 ...
Page 130
... bow shock , r * / R * N = universal gas constant = radius of the body = body nose radius ( same as R * ) = radius of the bow shock = coordinate along the bow shock , s * / R * T = T * = = ref u u V v ' X У α ε > ŏwo CY Ꮎ n ...
... bow shock , r * / R * N = universal gas constant = radius of the body = body nose radius ( same as R * ) = radius of the bow shock = coordinate along the bow shock , s * / R * T = T * = = ref u u V v ' X У α ε > ŏwo CY Ꮎ n ...
Page 167
... bow shock wave = wall condition S sh W = 15530 NO 8 stagnation - point conditions = derivative with respect to = transverse direction = dimensional freestream conditions Superscripts ( - ) = variable that has been normalized by the ...
... bow shock wave = wall condition S sh W = 15530 NO 8 stagnation - point conditions = derivative with respect to = transverse direction = dimensional freestream conditions Superscripts ( - ) = variable that has been normalized by the ...
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