Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Page 91
... enthalpy is given by HT = h + ( u2 + v2 ) / 2 ( 25 ) However , the specific relations for h for the two regions are different . For the precursor region , the relation for specific enthalpy is given by15 h = 1.4575 RT + ( 0.75 RT + D ) ...
... enthalpy is given by HT = h + ( u2 + v2 ) / 2 ( 25 ) However , the specific relations for h for the two regions are different . For the precursor region , the relation for specific enthalpy is given by15 h = 1.4575 RT + ( 0.75 RT + D ) ...
Page 114
... ENTHALPY , MJ / kg 80 60 40 20 20 ENTHALPY , MJ / kg 80 70 P = 10 atm 50 40 20 20 1 0 1000 2000 3000 4000 0 1000 TEMPERATURE , ° K a ) Pressure variation 3000 4000 2000 TEMPERATURE , ° K b ) H2 / He mixture Fig . 3 Enthalpy boundary ...
... ENTHALPY , MJ / kg 80 60 40 20 20 ENTHALPY , MJ / kg 80 70 P = 10 atm 50 40 20 20 1 0 1000 2000 3000 4000 0 1000 TEMPERATURE , ° K a ) Pressure variation 3000 4000 2000 TEMPERATURE , ° K b ) H2 / He mixture Fig . 3 Enthalpy boundary ...
Page 230
... enthalpy of 250 MJ / kg.12 Enthalpy radial distributions have yet to be determined ; however , preliminary spectroscopic data13 indicate that a peak - to - average ratio of about 2 might be expected , giving a centerline enthalpy of 500 ...
... enthalpy of 250 MJ / kg.12 Enthalpy radial distributions have yet to be determined ; however , preliminary spectroscopic data13 indicate that a peak - to - average ratio of about 2 might be expected , giving a centerline enthalpy of 500 ...
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/mē 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