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analysis analytic angle anharmonic appear application approach approximation atmosphere average body boundary calculations Center chapter Chem classical cloud coefficients collinear collision collision model color compared comparison complete configurations considered coupling cross section defined dependence described detailed determined developed diffusion discussed distribution dynamics effects eigenvalues energy transfer equation evaluated example exhaust Figure final flow forces formula function given included increase indicated initial integral interface layer limited maps matrix elements mean measured method molecular molecule motion NASA Note obtained oscillator output parameters particle Phys potential predictions present problem procedure produce quantum quantum mechanical range rate coefficients ratio recorder reduced reference Report represent rotational semiclassical separation shown shows similar solution Space step surface technique temperature theory tion trajectory transition probabilities transitions values variation vibrational
Page 45 - No. 12. Sponsoring Agency Name and Address 13. Type of Report and Period Covered National Aeronautics and Space Administration Technical Note Washington, DC 20546 14.
Page 41 - California 94035 11. Contract or Grant No. 12. Sponsoring Agency Name and Address 13. Type of Report and Period Covered National Aeronautics and Space Administration Washington, DC 20546 Technical Report 14.
Page 45 - Memorandum 14. SPONSORING AGENCY CODE 15. SUPPLEMENTARY NOTES Prepared by Space Sciences Laboratory, Science and Engineering 16.
Page 33 - ADPIC— A Three-Dimensional Computer Code for the Study of Pollutant Dispersal and Deposition Under Complex Conditions," Lawrence Livermore Laboratory, UCRL-51462 (1973).
Page 2 - CN curve with increasing angle of attack at the subsonic Mach numbers makes it extremely difficult to formulate a rational method for predicting Cyy throughout the high a range. This break is attributed to flow separation over the wing upper surface. For wings of generally lower aspect ratio and higher leading edge sweep than those studied here, the break has been attributed to vortex breakdown near the wing trailing edge of vortices shed from the leading edge. Vortex breakdown or bursting has been...
Page 49 - MM = 0.6 to 2.0. For several bodies of elliptic cross section, measured results are also predicted reasonably well over the investigated Mach number range from 0.6 to 2.0 and at angles of attack from 0° to 60°. As for the bodies of revolution, the predictions are best for supersonic Mach numbers. For body-wing and body-wing-tail configurations with wings of aspect ratios 3 and 4, measured normal-force coefficients and centers are predicted reasonably well at the upper test Mach number of 2.0. However,...
Page 41 - An engineering-type method is presented for computing normal-force and pitching-moment coefficients for slender bodies of circular and noncircular cross section alone and with lifting surfaces. In this method, a semi-empirical term representing viscous-separation crossflow is added to a term representing potential-theory crossflow.