Thermophysics of Spacecraft and Outer Planet Entry Probes: Technical Papers Selected from AIAA 14th Aerospace Sciences Meeting, January 1976, and the AIAA 11th Thermophysics Conference, July 1976 (with One Exception), Subsequently Revised for this VolumeAllie M. Smith, American Institute of Aeronautics and Astronautics |
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Page 81
... coefficient has been intro- duced in this investigation in a manner that allows utiliza- tion of the results of groove heat - transfer analyses to heat- pipe designs having differing wall thicknesses . The equivalent heat - transfer ...
... coefficient has been intro- duced in this investigation in a manner that allows utiliza- tion of the results of groove heat - transfer analyses to heat- pipe designs having differing wall thicknesses . The equivalent heat - transfer ...
Page 215
... coefficient meas- urements are summarized in Table 3. Measurements for the first experiment were time - averaged over a 20 - hr period ( 8 to 28 hr ) when the FRSI was heated to 48 ° C and were obtained by ratioing the time - averaged ...
... coefficient meas- urements are summarized in Table 3. Measurements for the first experiment were time - averaged over a 20 - hr period ( 8 to 28 hr ) when the FRSI was heated to 48 ° C and were obtained by ratioing the time - averaged ...
Page 330
... Coefficient ( cm - 1 ) 1000 100 10 Legend : S at 70 ° F ( 21 ° C ) 0.1 1 K at 70 ° F ( 21 ° C ) S at 2400 ° F ( 1316 ° C ) _ K at 2400 ° F ( 1316 ° C ) ↓ 0.01 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8 2.0 Wavelength microns -- Fig . 16 K - M ...
... Coefficient ( cm - 1 ) 1000 100 10 Legend : S at 70 ° F ( 21 ° C ) 0.1 1 K at 70 ° F ( 21 ° C ) S at 2400 ° F ( 1316 ° C ) _ K at 2400 ° F ( 1316 ° C ) ↓ 0.01 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8 2.0 Wavelength microns -- Fig . 16 K - M ...
Contents
Development of PhaseChange Systems | 19 |
Analysis of Axially Grooved HeatPipe Condensers | 37 |
GradedPorosity HeatPipe Wicks 15 | 57 |
Copyright | |
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ablation AIAA AIAA Paper analysis approximately atmosphere axial ballistic coefficient blade calculated carbon condensation cone half-angle configuration constriction resistance contact area convective convective heating cool coupled cryofilms crystal decrease dimensionless distribution drag coefficient engine entry probe equation exhaust plume experimental flow flowfield graphite groove heat flux heat pipe heat shield heat transfer heat-transfer heating environment hyperboloid incidence angles increase initial integral liquid louver mass loss material maximum measured melting microbalance NASA nose O/F ratio obtained optical Outer Planet outgassing outgassing rate parameter phase-change porosity presented in Fig problem radiant intensity radiation radiative heating rate radiative transfer region rocket Saturn shape change shock layer shown in Fig silica solar absorptance solution species spectral specular sphere cone stagnation point surface temperature thermal conductivity Thermophysics tion Uranus vapor pressure velocity wick