Accession Number : ADA325563

Title :   Receptivity Theory in Compressible Jet Flow Control.

Descriptive Note : Final rept.,

Corporate Author : ARIZONA UNIV TUCSON COLL OF ENGINEERING AND MINES

Personal Author(s) : Kerschen, Edward J.

PDF Url : ADA325563

Report Date : MAR 1997

Pagination or Media Count : 28

Abstract : An analysis is presented for the generation of shear layer instability waves by localized sources close to and far from the trailing edge. The frequency is assumed low enough that the shear layer can be represented by a vortex sheet, and the solution is developed using the Wiener-Hopf technique. Actuators (sources) on both surfaces of the splitter plate, and in the quiescent fluid just outside the shear layer, are considered. Results are presented for both subsonic and supersonic Mach numbers. Actuators on the stream side of the splitter place are found to be more effective in generating shear layer instability waves than actuators on the side adjacent to the quiescent fluid. The receptivity is highest for actuators located very near the trailing edge. For upstream actuators located on or near the splitter plate surface, the receptivity level decreases algebraically with distance from the trailing edge. In contrast, for actuators located just outside the shear layer downstream of the trailing edge, the receptivity level decreases exponentially with distance from the trailing edge.

Descriptors :   *FLOW SEPARATION, *AERODYNAMIC CONTROL SURFACES, SHEAR PROPERTIES, VORTICES, COMPRESSIBLE FLOW, ACTUATORS, MACH NUMBER, INSTABILITY, JET FLOW, TRAILING EDGES, JET MIXING FLOW.

Subject Categories : Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE