Accession Number : ADA290546

Title :   Interactions of Spanwise and Chordwise Vorticity Associated with Three-Dimensional Dynamic Stall Over an Oscillating Wing.

Descriptive Note : Final rept. 15 Feb 91-15 Aug 94,

Corporate Author : WASHINGTON STATE UNIV PULLMAN DEPT OF MECHANICAL AND MATERIALS ENGINEERING

Personal Author(s) : Ramaprian, B. R.

PDF Url : ADA290546

Report Date : 15 OCT 1994

Pagination or Media Count : 19

Abstract : This is the final report on the experimental research performed under U.S. Army Research Office Grant No. DAAL 03-91-0026, with Dr. Thomas Doligaiski as the Technical Program Manager. The Principal Investigator was B.R. Ramaprian. The research work involved the measurement of the pressure and velocity fields in the three-dimensional flow field surrounding and in the wake of the tip region of a rectangular wing of NACA 0015 profile. Measurements were made both with the wing stationary and with the wing oscillating sinusoidally in pitch about its quarter-chord axis. Pressure transducers and three-component laser Doppler velocimetry were used in these measurements. The results have been used to understand the vorticity dynamics in three-dimensional steady and unsteady flows. The study is relevant to helicopter rotor aerodynamics. All the data have been archived and are available for use by any interested reader.

Descriptors :   *VORTICES, *HELICOPTER ROTORS, *STALLING, *THREE DIMENSIONAL FLOW, VELOCITY, MEASUREMENT, ARMY RESEARCH, PRESSURE TRANSDUCERS, INTERACTIONS, DYNAMICS, ROTOR BLADES(ROTARY WINGS), FLOW FIELDS, RECTANGULAR BODIES, WIND TUNNEL TESTS, WAKE, UNSTEADY FLOW, FLOW SEPARATION, PRESSURE DISTRIBUTION, OSCILLATION, AERODYNAMICS, WING TIPS, STEADY FLOW.

Subject Categories : Aerodynamics
      Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE