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acoustic aerodynamic aircraft airplane amplitude angle of attack approximately axial-flow compressor back pressure beams characteristics chordwise COMMITTEE FOR AERONAUTICS compressor configuration constant crack cycles per second damper damping force decibels deflection design speed divergence boundaries drag coefficient drag force dynamic dynamic-response factor effect engine equation flap flight fluid free-field frequency hydro-skis inches increase incremental indicate inlet investigation Langley Aeronautical Laboratory Langley Field lift coefficient liquid temperature load Mach number maximum piston velocity measured NACA TN NATIONAL ADVISORY COMMITTEE noise nondimensional nose jet nozzle obtained parameter percent of design plane pressure ratio quasi-steady radius range reference Reynolds number rivet rotor shock strut shown in figure slip ratio specimens spectra spectrum spring force stall standard nozzle static static-pressure stator strain gages stringers supersonic surface tests thrust tion transfer function values variation vertical force viscosity wave drag weight flow wheel wing