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 |
From inside the book
Results 1-3 of 17
Page 172
... AIAA Journal , Vol . 6 , July 1968 , pp . 1362-1367 . 2 Wood , B. E. , Smith , A. M. , Roux , J. A. , and Seiber , B. A. , " Spectral Absolute Reflectance of CO2 Frosts from 0.5 to 12.0 μ , " AIAA Journal , Vol . 9 , July 1971 , pp ...
... AIAA Journal , Vol . 6 , July 1968 , pp . 1362-1367 . 2 Wood , B. E. , Smith , A. M. , Roux , J. A. , and Seiber , B. A. , " Spectral Absolute Reflectance of CO2 Frosts from 0.5 to 12.0 μ , " AIAA Journal , Vol . 9 , July 1971 , pp ...
Page 354
... AIAA 11th Thermophysics Conference, July 1976 (with One Exception), Subsequently Revised for this Volume Allie M ... Journal , Vol . 8 , Dec. 1970 , pp . 2152-2156 . 18 . Davis , R. T. , " Numerical Solution of the Hypersonic Viscous Shock - ...
... AIAA 11th Thermophysics Conference, July 1976 (with One Exception), Subsequently Revised for this Volume Allie M ... Journal , Vol . 8 , Dec. 1970 , pp . 2152-2156 . 18 . Davis , R. T. , " Numerical Solution of the Hypersonic Viscous Shock - ...
Page 431
... AIAA Journal , Vol . 9 , April 1971 , pp . 553-559 . 2Nicolet , W.E. , " Advanced Methods for Calculating Radiative Transport in Ablation - Product Contaminated Boundary Layers , " NASA CR - 1656 , Sept. 1970 . 3Wilson , K.H. ...
... AIAA Journal , Vol . 9 , April 1971 , pp . 553-559 . 2Nicolet , W.E. , " Advanced Methods for Calculating Radiative Transport in Ablation - Product Contaminated Boundary Layers , " NASA CR - 1656 , Sept. 1970 . 3Wilson , K.H. ...
Contents
Development of PhaseChange Systems | 19 |
Analysis of Axially Grooved HeatPipe Condensers | 37 |
GradedPorosity HeatPipe Wicks 15 | 57 |
Copyright | |
19 other sections not shown
Common terms and phrases
ablation absorption AIAA analysis angle application approximately assumed atmosphere axial body boundary calculated carbon coating coefficient conductivity cone configuration considered constant convective heating cool coupled crystal decrease determined developed distance distribution effect energy engine entry environment equation experiment experimental flow flux FRSI function given groove heat shield heating rates incidence included increase initial integral intensity layer liquid louver mass material maximum measured melting method nose obtained occurs optical outgassing parameter peak performance pipe Planet plume predicted present pressure probe problem properties radiation radiative heating range ratio reflectance region relative resistance respectively sample shape shock shown shown in Fig silica solar solid solution Space species spectral sphere surface Table temperature thermal thickness tion transfer vapor variation wall