NASA Technical NoteNational Aeronautics and Space Administration., 1960 |
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a,deg acceleration AERONAUTICS AND SPACE aileron airfoil airmail airspeed altitude angle of attack area ratio basic alloy blade boundary layer brake calculated characteristics CL,S Combustor length configurations constant contact angle contraction ratio crystallized glass ceramic CT,S Cx,s cylinder deflection deg deg deg drag coefficient Effect ejector tube equation experimental fatigue flap flight flow ft/sec glass ceramic heat helicopter Helicopter Rotor increase initial perigee injection velocity investigation Langley Field Langley Research Center lb/sq lift coefficient load longitudinal-force coefficient maximum measured minimum momentum NACA NACA TN NASA NATIONAL AERONAUTICS nozzle obtained operation parameter Pc/Pa percent perigee pitching pitching moment Pitching-moment presented in figure pressure primary-nozzle propeller reentry reference trajectory Reynolds number rotor shown in figure SPACE ADMINISTRATION specimen speed stagnation pressure tail temperature tests tion tip Mach number turbulent values vanadium variation vehicle velocity impulse zero
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