The Boeing Company

Eric Evin Adamson

David A Treiber

Spencer Robert Fugal

Michael R Schramm

Mithra M Sankrithi

Paul W Dees

Gerhard E Seidel

Adam P Malachowski

Chester P Nelson

Lawrence E Fink

Robert Hoffenberg

Edward W Gronenthal

V Kenneth Stuhr

Brian J O'Boyle

Alicia L Bidwell

Bonnie R Smith

Walter H Howard, Jr

Kenneth V Stuhr

A wing includes: an inner end configured to be coupled to a fuselage of an aircraft; an inboard section extending from the inner end; a fixed leading edge of the inboard section having a drooped contour positioned along at least a portion thereof; and an outboard section extending from the inboard section.

Wing, aircraft, and method for delaying wing stall of an aircraft

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.

Drag reduction device for exposed landing gear cavities

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.

Apparatus and method for reducing a sonic boom signature

An apparatus is formed of a cowl and a flow inlet formed on an interior surface of the cowl. The flow inlet has a supersonic compression section attached to a subsonic diffusion section at a throat. The supersonic compression section includes an at least partially elliptical compression ramp which extends along an approximately 180 degree arc along the interior surface. The flow inlet may form part of an aircraft. A method of air flow using the flow inlet is also disclosed.

Flow inlet

A supersonic inlet includes a supersonic section including a cowl which is at least partially elliptical, a ramp disposed within the cowl, and a flow inlet disposed between the cowl and the ramp. The ramp may also be at least partially elliptical.

Supersonic elliptical ramp inlet

A model adapter includes a first section of an off-body adapter at least partially circumscribing a sting mount, and a second section of the off-body adapter coupled to the first section such that the off-body adapter is coupled to the sting mount. The off-body adapter is positioned aft of the model to provide for a substantially aerodynamically smooth transition between a model and the sting mount.

Methods and systems for enabling wind tunnel models to transition between measuring aerodynamic forces and measuring acoustic signatures

A method for removing interference-induced distortion effects from an environment used to experimentally measure aerodynamic signatures. A space marching algorithm is used to extract the effects of environment including rail and wall reflections and rail edge effects to create an interference-free pressure signature.

Correction of pressure signals measured during supersonic wind tunnel testing

Integrated high-speed aircraft, such as high-speed transport aircraft, and associated methods of manufacture. In one embodiment, a high-speed transport aircraft includes a fuselage having a first fuselage portion and a second fuselage portion positioned aft of the first fuselage portion. The first fuselage portion can have a first cross-sectional area and the second fuselage portion can have a second cross-sectional area that is less than the first cross-sectional area. The high-speed transport aircraft can further include a wing and a propulsion system. The wing can extend outwardly from the fuselage at least proximate to the second fuselage portion and can include a leading edge region and a trailing edge region. The propulsion system can include an engine nacelle fixedly attached to the wing and laterally aligned with the second fuselage portion. In one aspect of this embodiment, the engine nacelle can include an air inlet positioned aft of the leading edge region of the wing and an exhaust gas outlet positioned aft of the trailing edge region of the wing.

Integrated high-speed aircraft and associated methods of manufacture

An improvement of a vertical fin (18) attached to a pylon strut (14) that is cantilevered from a wing rear spar (16) of a supersonic aircraft (9), the improved pylon (10) for mounting heavy assemblies such as an engine (8) to an aircraft wing (12). The fin (18) is a thin, elongate member having a ratio of fin height (36) to fin width (38) of about between 3:1 to 5:1. The ratio of fin length(34) to fin width (38) is preferably equal to or greater than 30:1. The fin at its lower surface (24) is attached to an upper surface (20) of the strut (14). The fin (18) preferably extends forward over a portion of the upper surface (22) of the wing (12) and is additionally attached thereto. One embodiment of a fin construction includes a U-shaped lower channel (40), an inverted U-shaped upper channel (42), a pair of substantially parallel upright sidewalls (32), an arcuate upper closeout member (46), and aerodynamic seals 48 as required. The area defined by the upright sidewalls (32) and the lower and upper channels (40), (42) is filled by a partitioned middle material (44), such as honeycomb core.

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Newcastle, WA, United States of America

Eric Evin Adamson