Dynamic Stall Measurements and Computations for a VR-12 Airfoil with a Variable Droop Leading Edge

Abstract

High density-altitude operations of helicopters with advanced performance and maneuver capabilities have lead to fundamental research on active high-lift system concepts for rotor blades. The requirement for this type of system was to improve the sectional lift-to-drag ratio by alleviating dynamic stall on the retreating blade while simultaneously reducing the transonic drag rise of the advancing blade. Both measured and computational results showed that a Variable Droop Leading Edge (VDLE) airfoil is a viable concept for application to a rotor high-lift system. Results are presented for a series of 2D compressible dynamic stall wind tunnel tests with supporting CFD results for selected test cases. These measurements and computations show a dramatic decrease in the drag and pitching moment associated with severe dynamic stall when the VDLE concept is applied to the Boeing VR-12 airfoil. Test results also show an elimination of the negative pitch damping observed in the baseline moment hysteresis curves.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 2003
Accession Number
ADA480698

Entities

People

  • K. W. Mcalister
  • M. S. Chandrasekhara
  • P. B. Martin
  • W. Geissler

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Mechanics
  • Frequency
  • Helicopters
  • High Density
  • High Lift
  • Leading Edges
  • Measurement
  • Numerical Analysis
  • Pressure Distribution
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Computational Fluid Dynamics (CFD)