The Boeing Company

Philippe R Spalart

Jeffrey D Crouch

Hugh Poling

Brandon L Bertolucci

Jerald C Baillie, Jr

Stephen T LeDoux

Gail Mary Barker

Randal H Smith

Jerald C Baillie

Stephen T Ledoux

Gail M Barker

A window assembly for an aircraft is provided that includes a windshield, a side window, a post, and an airflow surface. The windshield is oriented toward a front of the aircraft. The side window is oriented toward a side of the aircraft. The post is interposed between the windshield and the side window. The airflow surface is disposed on the post and on an exterior of the aircraft. The airflow surface extends along a length from a leading edge proximate the windshield to a trailing edge proximate the side window, and extends along a height between a top and a bottom. The airflow surface has a first radius of curvature proximate the leading edge and a second radius of curvature proximate the trailing edge, wherein the first radius of curvature is less than the second radius of curvature.

Apparatuses and methods for aerodynamic window assemblies

A windshield wiper arm is provided on an outside of an aircraft and positioned to directly engage an air flow while the aircraft is traveling. The wiper arm includes an arm portion coupled to the aircraft and having an arm exterior surface, the arm portion extending along an arm axis and defining an arm length. A bead extends outwardly from the arm exterior surface and defines a bead exterior surface, the bead being sized sufficiently to engage a boundary layer of the air flow. A wiper blade is coupled to the arm portion. The bead prevents separation of the boundary layer from the arm exterior surface, thereby to attenuate shedding of vortices and associated vibrations and noise.

Vehicle external component having reduced vortex shedding

An active control method and apparatus for encouraging the early destruction of trailing vortices formed by a lifting body having at least two control surfaces on each side and creating multiple vortex pairs is provided. The method includes actuating the control surfaces in a manner leading to the direct excitation of one or more of the Transient Growth Mechanism, the Short Wavelength Instability, the Long Wavelength Instability, and the Crow Instability to result in the accelerated breakup of the trailing vortices. A method of selecting control parameters in an active control system includes identifying the near-field vorticity distribution of the aircraft, selecting at least one amplification mechanism for distorting the trailing vortices, determining amplitudes and wavelengths for imposed vortex perturbations, simulating trailing vortex evolutions, determining effectiveness of perturbations and amplification mechanisms, determining vortex positions as a function of control surface deflections, and determining control parameters to govern the movement of the wing control surfaces.

Active system for early destruction of trailing vortices

Growing community of inventors

Seattle, WA, United States of America

Philippe R Spalart