Accession Number : ADA474073


Title :   Experimental Analysis of the Vorticity and Turbulent Flow Dynamics of a Pitching Airfoil at Realistic Flight Conditions


Descriptive Note : Final rept. 1 May 2003-31 May 2007


Corporate Author : TEXAS A AND M UNIV COLLEGE STATION


Personal Author(s) : Bowersox, Rodney D ; Sahoo, Dipankar


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a474073.pdf


Report Date : 31 Aug 2007


Pagination or Media Count : 153


Abstract : The primary objective of this research proposal was improved understanding of the fundamental vorticity and turbulent flow physics for a dynamically stalling airfoil at realistic helicopter flight conditions. To meet this objective, an experimental program using high-resolution particle image velocimetry was performed. High-resolution planar contours of the instantaneous and mean velocity field on a dynamically pitching NACA 0012 airfoil operating in the Texas A&M University large-scale wind tunnel are planned. For the present study, the Mach number, chord Reynolds number, and reduced frequency were selected as 0.2/0.3, 2.0/2.8x106 and 0.1/0.18, respectively. The test matrix included static attached, static stall, light dynamic stall and deep dynamic stall. The goal of these analyses was improved understanding of the dynamic stall processes at realistic flight conditions. The velocity data was processed to examine the vorticity and turbulent transport near the leading edge during stall. The data from this study are summarized in this report.


Descriptors :   *TURBULENT FLOW , *VORTICES , *STALLING , *AIRFOILS , VELOCITY , PHYSICS , PLANAR STRUCTURES , REYNOLDS NUMBER , PARTICLE IMAGE VELOCIMETRY , LEADING EDGES , FLIGHT , HELICOPTERS , HIGH RESOLUTION , PITCH(MOTION) , DYNAMICS


Subject Categories : Military Aircraft Operations
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE