Dynamic Stall Penetration Experiments on a Swept Wing

Abstract

An experiment was conducted to study the aerodynamic response of a wing to large amplitude pitching motions, including dynamic stall. A two- dimensional model was tested at Mach numbers of 0.2, 0.3, and 0.4, corresponding to Reynolds numbers between 2 x 1000000 and 4 x 1000000. A total of 49 unsteady conditions were studied, including both sinusoidal oscillations and constant pitch rate ramps. The ramp motions ranged up to 0 to 30 deg at pitch rates between 17.5 and 350 deg/sec. A preliminary analysis of the results shows significant effects of pitch rate and Mach number on the surface pressures, integrated airloads, and locations of boundary layer transition and separation. A pressure oscillation was detected in the post stall region that appears to result from periodic vortex shedding that has synchronized to the imposed pitching motion. A more detailed analysis of these results will be conducted during the remainder of this activity. Keywords: Unsteady aerodynamics; Dynamic stall; Aerodynamic testing; Unsteady measurement techniques.

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Document Details

Document Type
Technical Report
Publication Date
Sep 12, 1986
Accession Number
ADA174962

Entities

People

  • Franklin O. Carta
  • Peter F. Lorber

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Boundary Layer Transition
  • Data Acquisition
  • Flow
  • Fluid Flow
  • Heat Transfer
  • Layers
  • Mach Number
  • Mechanical Phenomena
  • Pressure Transducers
  • Skin Friction
  • Three Dimensional
  • Trailing Edges
  • Two Dimensional
  • Vortex Shedding
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.