A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing

Abstract

This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds numbers of 600,000 and 900,000. The force and moment results achieved indicate supercirculation was not present. Flow visualization with nylon tufts displayed extreme flow disruption at the trailing edge, due to free-stream impingement on both the sting and blowing air supply hoses. The available blowing air supply was not strong enough to produce a jet flow with the momentum needed to overcome this disruption. Wing model design changes were recommended to alleviate this problem.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1989
Accession Number
ADA216248

Entities

People

  • John W. Trainor

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Supplies
  • Aircrafts
  • Boundary Layer
  • Engineering
  • Flow Visualization
  • Fluid Dynamics
  • Free Stream
  • Jet Flow
  • Measurement
  • Mechanics
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Short Takeoff Aircraft
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.