## NACA technical note, Volumes 3663-3675 |

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aerodynamic Ames Aeronautical Laboratory angle of attack angle of bank aspect ratio axial base diameter Basic body blockage bodies of revolution boundary layer calculated camber cascade chord configuration cross-section area cruciform wing curve cylinder deflector diffuser discharge coefficient distribution downstream drag-rise duct effect engine speed equation fineness ratio free-stream function fuselage hemisphere hole inch indented inlet investigation lift coefficient Mach number mass-flow ratio maximum measured method modified NACA RM NACA TN nacelle nozzle pressure ratio obtained percent perforated sheet performance permeability Pitching-moment coefficient plane pressure coefficient radius reference region reverse-thrust ratio ring Sears-Haack body shown in figure sketch slope STANFORD UNIVERSITY LIBRARIES static pressure subsonic supersonic surface swept wing symmetrical target target-type temperature theory thrust reverser tion total-pressure transonic area rule transonic similarity rule upflow angle upwash values variation velocity vortex vortices wall thickness wave drag wing-body combinations zero lift