Abstract: A wing of an aircraft that includes a wing leading edge, a wing trailing edge, and a wing surface defined by a wing upper surface and a wing lower surface is described herein. The wing extends from the wing root to the wingtip, and the wingtip has a wingtip chord. A winglet extends from the wingtip and has a winglet leading edge, a winglet trailing edge, a winglet inboard surface, a winglet outboard surface, a winglet root having a winglet root chord, and a winglet tip. A flow fence is disposed on the wing surface inboard from the winglet and overlapping with the winglet. The flow fence is adapted to delay and/or prevent airflow separation on the winglet inboard surface at high angle of sideslip, increasing lateral stability and linearizing aircraft behavior at high angle of sideslip.

Abstract: A wing of an aircraft that includes a wing leading edge, a wing trailing edge, and a wing surface defined by a wing upper surface and a wing lower surface is described herein. The wing extends from the wing root to the wingtip, and the wingtip has a wingtip chord. A winglet extends from the wingtip and has a winglet leading edge, a winglet trailing edge, a winglet inboard surface, a winglet outboard surface, a winglet root having a winglet root chord, and a winglet tip. A flow fence is disposed on the wing surface inboard from the winglet and overlapping with the winglet. The flow fence is adapted to delay and/or prevent airflow separation on the winglet inboard surface at high angle of sideslip, increasing lateral stability and linearizing aircraft behavior at high angle of sideslip.

Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: A pedal operated apparatus controls an aircraft rudder during flight using a mechanical linkage and controls a nose wheel power steering system while the aircraft is on the ground. The apparatus includes a pair of foot pedals operatively connected to the rudder and also connected to the power steering system. Springs are operatively connected to the pedals only when the aircraft is on the ground to center the nose wheel after a turn. The springs are operatively disconnected when the aircraft is in flight.

Abstract: A pedal operated apparatus controls an aircraft rudder during flight using a mechanical linkage and controls a nose wheel power steering system while the aircraft is on the ground. The apparatus includes a pair of foot pedals operatively connected to the rudder and also connected to the power steering system. Springs are operatively connected to the pedals only when the aircraft is on the ground to center the nose wheel after a turn. The springs are operatively disconnected when the aircraft is in flight.

Abstract: An upper wing surface of a laminar-flow airfoil for decreasing an undesirable head-lowering pitching moment around an aerodynamic center of the airfoil. The upper wing surface includes: a convex front profile portion extending from a leading edge to a largest-thickness point located corresponding to 38% of a wing chord length. A convex central profile portion extends from the largest-thickness point to a position corresponding to 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of the wing chord from the largest-thickness point is equal to or smaller than 0.12. A concave rear profile portion extends from a position corresponding to 95% of the wing chord length to the trailing edge. The rear profile portion forms a pressure gradient is steeper than that formed by the central profile portion.

Abstract: A main wing structure comprises at least a leading edge structure and a wing central structure coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface, a lower wing surface, a leading edge and a trailing edge. The upper wing surface includes: a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located at 38% of a wing chord length; a central profile portion which has a positive curvature radius, and which is provided to extend from the largest-thickness point to the vicinity of a position corresponding to approximately 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of a wing chord from the largest-thickness point is equal to or smaller than 0.

Abstract: An upper wing surface of a laminar-flow airfoil includes: a front profile portion which has a positive curvature radius, and which is provided to extend from a leading edge to a largest-thickness point located at a position corresponding to 38% of a wing chord length. The front profile portion forms a laminar-flow boundary layer. A central profile portion has a positive curvature radius and is provided to extend from the largest-thickness point to the vicinity of a position corresponding to 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of the wing chord from the largest-thickness point is equal to or smaller than 0.12.

Abstract: A main wing structure comprises at least a leading edge structure and a wing central structure coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface, a lower wing surface, a leading edge and a trailing edge. The upper wing surface includes: a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located at 38% of a wing chord length; a central profile portion which has a positive curvature radius, and which is provided to extend from the largest-thickness point to the vicinity of a position corresponding to approximately 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of a wing chord from the largest-thickness point is equal to or smaller than 0.

Abstract: It is an object of the present invention to reduce the wave resistance by disposing a fluid element such as an engine nacelle in a predetermined position on the upper surface of the main wing, and positively superposing the air flow generated by the fluid element onto the air flow on the upper surface of the main wing, thereby reducing the peak of the negative pressure on the upper surface of the main wing to retard the generation of a shock wave. If the engine nacelle is disposed on the upper surface of the main wing, and the longitudinal position of the front end of the engine nacelle is established in a range of 63% to 100% from the front end of a wing chord of the main wing (see b and i in FIG. 9), a shock wave is generated on the upper surface of the main wing in a range of transonic speed to inhibit an increase in wave resistance, whereby the cruising speed can be increased, while avoiding an increase in amount of fuel consumed.