Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 60
... given by nel ( B8 ) where no , max δ max 2 = 13.6 / n , max ( B9 ) is 6. This maximum reduction is necessary so as ... given by ( B10 ) × S = 1.10 × 10-16 + né 2 No exp [ -157,780 ( 1 - - 2- ) ) ( B11 ) and ( v ) ( ev1 ) is the ...
... given by nel ( B8 ) where no , max δ max 2 = 13.6 / n , max ( B9 ) is 6. This maximum reduction is necessary so as ... given by ( B10 ) × S = 1.10 × 10-16 + né 2 No exp [ -157,780 ( 1 - - 2- ) ) ( B11 ) and ( v ) ( ev1 ) is the ...
Page 75
... given previously . Results for 0-0 , C - H , C - 0 , and H - 0 are given in Table 7 . The translational contributions to the thermal conduc tivity of a multicomponent gas mixture , xmix , is given by21 X tr where Lii X xmix 0 = 4 tr Lij ...
... given previously . Results for 0-0 , C - H , C - 0 , and H - 0 are given in Table 7 . The translational contributions to the thermal conduc tivity of a multicomponent gas mixture , xmix , is given by21 X tr where Lii X xmix 0 = 4 tr Lij ...
Page 132
... given in Ref . 2. There are , however , a few definite changes in the governing equations because of the chemical nonequilibrium condition , and these are discussed briefly in this section . Governing Equations for the Precursor Region ...
... given in Ref . 2. There are , however , a few definite changes in the governing equations because of the chemical nonequilibrium condition , and these are discussed briefly in this section . Governing Equations for the Precursor Region ...
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 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 Progress in Astronautics 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