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aerodynamic characteristics AERONAUTICS AND SPACE afterbody angle of attack blade Bottom topography approximated calculated camber centimeters characteristics closed coating coefficient collector collector panels Concluded configuration Continued core corr decayer deflection DELAWARE BAY determined diameter diffuse direct distribution drag Effect engine exhaust exit field Figure flow flow rate fuselage heat HRE model impact impingement increase indicated initial inlet least squares technique lift liquid load located longitudinal aerodynamic Mach number manifolds maximum measured NASA nautical miles nozzle obtained operation percent Performing points position presented pressure pressure ratio PUBLICATIONS range ratio reference Report Research Center screen seat seconds shown in figure shows simulated solar energy solar radiation speed stabilized station surface tail tank TECHNICAL temperature transition tunnel V/STOL values variation velocity wing Y-axis
Page 14 - Jones, WL: Effect of Exhaust Nozzle Configuration on Aerodynamic and Acoustic Performance of an Externally Blown Flap System with a Quiet 6:1 Bypass Ratio Engine.
Page 27 - HEAT-TRANSFER DISTRIBUTIONS ON A 0.013-SCALE SHUTTLE SOLID ROCKET BOOSTER AT MACH 3.70 AND ANGLES OF ATTACK FROM 0° TO 180° Milton Lamb and Robert L.
Page 90 - Proposed Standard Solar-Radiation Curves for Engineering Use", J. Franklin Inst.. vol. 230, No.