Accession Number : ADA326174
Title : Unsteady Three-Dimensional Aerodynamic Flow.
Descriptive Note : Final technical rept. 15 Feb 95-14 Feb 97,
Corporate Author : LEHIGH UNIV BETHLEHEM PA DEPT OF MECHANICAL ENGINEERING AND MECHANICS
Personal Author(s) : Rockwell, Donald
PDF Url : ADA326174
Report Date : 28 FEB 1997
Pagination or Media Count : 7
Abstract : The overall objective of this program is to determine the instantaneous flow structure on delta wings at high angle of attack as well as from cylindrical bodies, which are subjected to basic classes of motion. New techniques of high image density particle image velocimetry provide the instantaneous vorticity fields and streamline patterns, thereby allowing interpretation of the underlying physics using critical point theory. This type of quantitative interpretation of the flow structure is crucial for performing vorticity balances on wings and bodies and thereby optimization of overall performance characteristics. Furthermore, for the case of the delta wing at high angle of attack, local control techniques are applied simultaneously at leading and trailing edges of the wing, in order to alter the crucial features of vortex breakdown and subsequent large scale stall. Such control techniques have application to a wide variety of separated flows from wings and cylindrical bodies.
Descriptors : *MANEUVERABILITY, *TOPOLOGY, *DELTA WINGS, PERFORMANCE(ENGINEERING), VORTICES, STALLING, CYLINDRICAL BODIES, LEADING EDGES, UNSTEADY FLOW, FLOW SEPARATION, POINT THEOREM, AERODYNAMICS, HIGH ANGLES, TRAILING EDGES, THREE DIMENSIONAL FLOW.
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE