Outer Planet Entry Heating and Thermal ProtectionRaymond Viskanta |
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Results 1-3 of 72
Page 250
... shown in Fig . 3. The identified lines of Si are indicated in the figure . The two lines identified with the Roman numeral II are from the ionized silicon Si + . The reference constant intensity curve shown in the figure was obtained by ...
... shown in Fig . 3. The identified lines of Si are indicated in the figure . The two lines identified with the Roman numeral II are from the ionized silicon Si + . The reference constant intensity curve shown in the figure was obtained by ...
Page 363
... shown in Fig . 13. The base enthalpy is approximately 30-40 % lower than the total enthalpy , and the peak base pressure is less than 0.1 atm . The distribution of the predicted radiative and convective heat - transfer rates is shown in Fig ...
... shown in Fig . 13. The base enthalpy is approximately 30-40 % lower than the total enthalpy , and the peak base pressure is less than 0.1 atm . The distribution of the predicted radiative and convective heat - transfer rates is shown in Fig ...
Page 382
... shown in Fig . 9b as a function of the number of cases . This is the error between the computed value ( Fig . 8 ) and the limits of the 90 % confidence interval in Fig . 9a . The maximum error is very large for less than 25 cases but is ...
... shown in Fig . 9b as a function of the number of cases . This is the error between the computed value ( Fig . 8 ) and the limits of the 90 % confidence interval in Fig . 9a . The maximum error is very large for less than 25 cases but is ...
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 | |
18 other sections not shown
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