Abstract: An exposed main landing gear cavity in a bottom wall of an aircraft fuselage may include a main landing gear cavity outer ring recessed within the fuselage and having an inner surface encircling the main landing gear cavity, first baffle extending inward from the outer ring inner surface at an aft and inboard position on the inner surface, and a second baffle extending inward from the outer ring inner surface at an aft and outboard position on the outer ring inner surface. The main landing gear cavity may further include an aft fairing disposed proximate the outer ring bottom edge of the outer ring and connected to the fuselage at an aft side of the main landing gear cavity. An aft fairing top surface may have curvature causing the top surface to extend downward away from the outer ring as the top surface extends inward away from the outer ring.

Abstract: An exposed main landing gear cavity in a bottom wall of an aircraft fuselage may include a main landing gear cavity outer ring recessed within the fuselage and having an inner surface encircling the main landing gear cavity, first baffle extending inward from the outer ring inner surface at an aft and inboard position on the inner surface, and a second baffle extending inward from the outer ring inner surface at an aft and outboard position on the outer ring inner surface. The main landing gear cavity may further include an aft fairing disposed proximate the outer ring bottom edge of the outer ring and connected to the fuselage at an aft side of the main landing gear cavity. An aft fairing top surface may have curvature causing the top surface to extend downward away from the outer ring as the top surface extends inward away from the outer ring.

Abstract: An apparatus and method using an interference body to shape a sonic boom signature is provided herein. The interference body can be installed on various control surfaces, including a vertical control surface. The interference body can be sized and positioned to create a desired amount of interference with expansion wave s generated by one or more components of an aircraft. In one configuration, the interference body can be operative to reduce the sonic boom formed by an aircraft operating at or above supersonic speeds.

Abstract: An airfoil for use on a high speed, jet powered airborne mobile platform and secured to an exterior surface of said mobile platform at a location so as to be disposed within a boundary layer during flight of the mobile platform. The airfoil produces a peak Mach number for airflow over a longitudinal centerline of said airfoil that is no greater than about Mach 1.2 when said mobile platform is moving at a speed of about Mach 0.85 with a relative constant Mach number flow over a region defined as at least an approximate 20% length of maximum thickness of said airfoil. The airfoil also has a pressure distribution (Cp) that is positive at a trailing edge thereof.

Abstract: A fairing suitable for enclosing a component mounted on an exterior surface of a mobile platform, and more particularly on an outer surface of a high speed mobile platform such as a jet aircraft or an aerospace vehicle. The fairing provides aggressive closure angles for optimum RF performance when used to house an antenna that is scanned to varying azimuth and elevation angles. The fairing further provides low aerodynamic drag, is scalable to enclose components having wide ranging dimensions, and provides attached flow with minimum separation of airflow thereover for airflows experienced by high speed jet aircraft, and reduces or eliminates RF reflections within the fairing from the RF beam of the antenna.

Abstract: A fairing suitable for enclosing a component mounted on an exterior surface of a mobile platform, and more particularly on an outer surface of a high speed mobile platform such as a jet aircraft or an aerospace vehicle. The fairing provides aggressive closure angles for optimum RF performance when used to house an antenna that is scanned to varying azimuth and elevation angles. The fairing further provides low aerodynamic drag, is scalable to enclose components having wide ranging dimensions, and provides attached flow with minimum separation of airflow thereover for airflows experienced by high speed jet aircraft, and reduces or eliminates RF reflections within the fairing from the RF beam of the antenna.

Abstract: An airfoil for use on a high speed, jet powered airborne mobile platform and secured to an exterior surface of said mobile platform at a location so as to be disposed within a boundary layer during flight of the mobile platform. The airfoil produces a peak Mach number for airflow over a longitudinal centerline of said airfoil that is no greater than about Mach 1.2 when said mobile platform is moving at a speed of about Mach 0.85 with a relative constant Mach number flow over a region defined as at least an approximate 20% length of maximum thickness of said airfoil. The airfoil also has a pressure distribution (Cp) that is positive at a trailing edge thereof.

Abstract: An airfoil for use with high speed mobile platforms. The airfoil features include low peak local mach numbers over the surface avoiding shock, uniform pressure distribution across the entire flight regime, aggressive closure angles for good RF performance, and a scaleable fillet to reduce the stagnation flow region at a leading edge of the airfoil. The airfoil has a scaleable contour for variation in length, height, and length-to-height ratio while maintaining excellent aerodynamic characteristics.