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aerodynamic AERONAUTICS TECHNICAL NOTE aileron airfoil airplane alloys aluminum amplitude angle of attack axis beam of light blade boundary buzz calculated center-of-gravity chord coating COMMITTEE FOR AERONAUTICS contact flow copper crack curve disk loading dislocation displacement downwash effect elevator deflection required equation experimental flame front flap flight tests frequency grain-boundary horizontal tail hot-wire increase indicated airspeed induced velocity initial internal friction investigation Langley Aeronautical Laboratory Langley Field lift coefficient low-wing Mach number maximum measured microseconds NACA NACA TN NATIONAL ADVISORY COMMITTEE notched observed obtained oscillation peak percent plane plate power-off pressure waves ratio rearward reference reflected shock front reflected transmitted shock saiavaan satisfactory lateral control servovane control shadowgraphs shear shear modulus shock tube shock wave shown in figure slipstream spanwise specimens speed strain stress temperature tion transmitted shock front transmitted shock wave turbulent contact values vane wake wing zero