Accession Number : ADA289802

Title :   A Nonintrusive Method of Quantifying Flow Visualization Data in Vortex Flow Fields.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s) : Sei, Vincent J.

PDF Url : ADA289802

Report Date : DEC 1994

Pagination or Media Count : 86

Abstract : The High Angle of Attack Research Vehicle (HARV) as well as other similar flight test aircraft have been using smoke flow visualization techniques to characterize the vortex flow created by leading edge extensions and the forebody. With the advent of video measurement techniques, this type of flow visualization can not only provide a qualitative assessment of the flow but also a quantitative measure to be used to validate computational fluid dynamic codes and wind tunnel test. One of the major drawbacks to employing video imaging was the introduction of false motion due to camera movement in flight. A relative motion approach using fixed targets along with the flow visualization scheme was utilized to remove unwanted motion. The relative motion algorithm was tested using a laboratory test setup where cameras underwent both translational and rotational motion to simulate both wing bending and torsion. The method was effective in removing both motions with only a slight loss of accuracy. (AN)

Descriptors :   *FLOW VISUALIZATION, *FLOW FIELDS, ALGORITHMS, FLIGHT TESTING, MANEUVERABILITY, EXPERIMENTAL DATA, COMPARISON, ACCURACY, THESES, VORTICES, COMPUTATIONAL FLUID DYNAMICS, ANGLE OF ATTACK, BENDING, IMAGES, WIND TUNNEL TESTS, JET FIGHTERS, LEADING EDGES, DYNAMIC PROGRAMMING, VIDEO SIGNALS, WING BODY CONFIGURATIONS, PRESSURE DISTRIBUTION, AERODYNAMIC LIFT, TORSION, MOTION PICTURE CAMERAS.

Subject Categories : Fluid Mechanics
      Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE