Abstract: Multi-positional tail skid assemblies and methods for their use. In one embodiment, a multi-positional tail skid assembly includes a skid member and a skid deployment system operably connected to the skid member. The skid member can include a first portion attachable to an aft portion of a fuselage and a second portion movable relative to the aft portion of the fuselage. The second portion can support a skid surface configured to contact a surface of a runway. The skid deployment system can be configured to move the skid surface between first and second positions. When the skid surface is in the first position, the skid surface is closer to the aft portion of the fuselage than when the skid surface is in the second position.

Abstract: Multi-positional tail skid assemblies and methods for their use. In one embodiment, a multi-positional tail skid assembly includes a skid member and a skid deployment system operably connected to the skid member. The skid member can include a first portion attachable to an aft portion of a fuselage and a second portion movable relative to the aft portion of the fuselage. The second portion can support a skid surface configured to contact a surface of a runway. The skid deployment system can be configured to move the skid surface between first and second positions. When the skid surface is in the first position, the skid surface is closer to the aft portion of the fuselage than when the skid surface is in the second position.

Abstract: A sealing device (20) for an airplane (22). The airplane having a wing (24) and a first engine nacelle (26) attached to the wing. The wing having a wing root, a wing tip, a leading edge, a trailing edge and at least a first flap (30b) operatively connected to the leading edge. The flap being actuatable between a retracted position and an extended position. The flap in the extended position defining a gap between the flap and engine nacelle. The sealing device includes a body attached to the engine nacelle. The body having a forward portion (54), a center portion (56) and an aft portion (58). The body being positioned on the engine nacelle to contact the flap when the flap is in the extended position and forming a seal between the flap and nacelle to improve aerodynamic efficiency of the wing. The seal is formed by the flap being nested within the center portion of the body when the flap is in the extended position.

Abstract: A method and apparatus for reducing noise produced by the airframe of an airplane in flight. The present invention provides a smooth, continuous, arcuate surface, such as a rounded edge cap, for the lateral surface of any airplane flap exposed to fluid having relative motion with respect to the airplane. Tests indicate that a rounded flap edge cap made in accordance with the present invention is effective in attenuating noise levels in the middle and high frequency range, i.e., between about 500 to about 10000 Hz.

Abstract: In a wing and nacelle combination, where the nacelle is positioned below and forwardly of the wing leading edge, a wake control device to control a turbulent wake which is formed at the upper forward lip portion of the nacelle. This wake control device comprises a forward vortex generating portion to create a vortex which travels over the leading edge of the wing, and also a fence located at the middle third of the nacelle to control boundary layer air and thus properly locate the wake control vortex.