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aerodynamic aileron airfoil altitude amplitude angle of attack angle of dead approximately boundary layer calculated chord comparison curves dead rise dead spot dead-rise deceleration decrease delta wings determined distance drag coefficient due to sideslip Dutch roll effect equation experimental flow frequency gust-alleviation increase indicated investigation jet transport laminar Langley Aeronautical Laboratory Langley Field lb/sq leading edge lift coefficient Mach number maximum method motion NACA TN nondimensional normal-force coefficient obtained oscillation parameter percent plane power spectral density pressure distributions pressure rise radians range reference Reynolds number rolling gusts second wheel semispan drooped separation servo shown in figure side force side gusts sidewash span load spray stability static supersonic surface test series test vehicle tion tire inflation pressure trailing edge true airspeed tunnel type 1 autopilot values variation vertical load vertical tire deflection vertical velocities vortex wheel to contact yaw angle yawed-rolling