An Experimental Investigation of High Lift/High Rate Aerodynamics of an Unsteady Airfoil

Abstract

An experimental study of a two dimensional NACA 0015 airfoil undergoing both positive and negative constant pitch rate motions at high angles of attack was conducted in the Ohio University tow tank facility. Nondimensional pitch rates in the range of 0.1 < K < 0.7 and Reynolds numbers in the range of 141,000 < Re < 342,000 were considered. Test results consist of lift and drag force coefficients and flow visualizations. The results of this study provide insight into the airfoil-dynamic stall vortex interaction during the pitch down motion and the cessation of aerodynamic stall. These data may be useful in high angle of attack applications such as the enhanced maneuverability concept for fighter aircraft. Keywords: Unsteady aerodynamics, Pitching airfoils, Maneuverability.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1989
Accession Number
ADA206964

Entities

People

  • G. M. Graham

Organizations

  • Ohio University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamics
  • Boundary Layer
  • Brushless Dc Motors
  • Classification
  • Coefficients
  • Fighter Aircraft
  • Flow
  • Flow Visualization
  • Fluid Dynamics
  • High Angles
  • High Lift
  • Maneuverability
  • Measurement
  • Reynolds Number
  • Security
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Marine Hydrodynamics