The Boeing Company

Daniel Paul Brzozowski

Steven Fulton Griffin

Michael L Sangwin

Zachariah B VanDeMark

Bradley Jerome Rafferty

Nathan Owen Packard

Robert M Dowgwillo

Zachariah B Vandemark

Hin-Fan M Lau

Jay Wiggins

Frederick W Roos

A test fixture for measuring the skin friction of anisotropic surface finish on a material is described. The test fixture can be utilized in a wind tunnel. The test fixture can include a plate having a cavity configured to receive a circular specimen disk. A motor can be coupled to the plate to rotate the circular specimen disk. During a test, a fluid can flow over the plate in a particular direction and the motor can rotate the circular specimen disk to determine the effect of the flow angle on the average skin friction coefficient of a surface finish of a material. The circular specimen disk can easily be attached and detached from the test fixture to allow circular specimen disks with different surface finishes to be tested.

Test fixture to measure the average skin friction of anisotropic surfaces

A device including a resonant array of a plurality of synthetic jet generators where neighboring jet generators are coupled, resulting in the potential for constructive and destructive interference between jets of the plurality of synthetic jet generators depending on the relative phase of a corresponding plurality of drive signals to plurality of synthetic jet generators. The device also includes a controller configured to control the relative phase of the corresponding plurality of drive signals to effect a change in a first jet emitted by a first synthetic jet generator of the plurality of synthetic jets by changing a given phase of a second jet emitted by a second synthetic jet generator of the plurality of synthetic jet generators.

Phase tailoring for resonant flow devices

Thrust-reverser assemblies that utilize active flow-control and systems and methods including the same are disclosed herein. The thrust-reverser assemblies define a forward-thrust configuration and a reverse-thrust configuration. The thrust-reverser assemblies include a bullnose fairing that defines a portion of a reverser duct and an active flow-control device. The active flow-control device is located to energize a boundary layer fluid flow within a boundary layer that is adjacent to the bullnose fairing to resist separation of the boundary layer from the bullnose fairing when the thrust-reverser assembly is in the reverse-thrust configuration. The methods include flowing a thrust-reverser fluid stream through the reverser duct to generate the boundary layer and energizing a boundary layer fluid flow within the boundary layer with an active flow-control device to resist separation of the boundary layer from the bullnose fairing.

Thrust-reverser assemblies that utilize active flow-control and systems and methods including the same

Growing community of inventors

Ladue, MO, United States of America

Daniel Paul Brzozowski