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aerodynamic section characteristics afterbody keel aileron adverse yawing airfoil chord airfoil section airplane angle of afterbody angle of attack beam buckling center of gravity Committee for Aeronautics contours critical compressive stress critical stress dead rise decreased depth of step determined dihedral angle double slotted flap drag coefficient effective dihedral equation flanges flap deflection flying boats fore flap Fowler flap full-size fuselage gross weight increasing trim increment instability investigation Langley Field length of afterbody limits of stability load lower limit lower trim limit maximum lift maximum section lift mechanical advantage Memorial Aeronautical Laboratory motion NACA NATIONAL ADVISORY COMMITTEE O I I I obtained optimum percent plain airfoil plan form porpoising ratio rear flap section lift coefficient shear stress shown in figure sideslip single slotted flaps speeds stable positions stick forces tail length tests tion trailing edge turret upper limit values variation ventilation vertical—tail area WARTIME REPORT wing