An Experimental Study of a Sting-Mounted Single-Slot Circulation Control Wing

Abstract

This wind tunnel study investigated the feasibility of using a sting and force balance to measure the aerodynamic forces and moments on a circulation control wing. A 20% this, 8.5% camber, single blowing slot, rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift and drag coefficients were referenced to the stability axis. The Reynolds number for all tests was 950,000; angle of attack was varied from -6 to +6 degrees. Trends in the data were similar to two dimensional data, with the exception of high drag coefficients with increased blowing. Results show it is feasible to test three dimensional wings using a sting and force balance if appropriate data corrections are applied.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1990
Accession Number
ADA229867

Entities

People

  • Michael E. Pelletier

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Supplies
  • Aircrafts
  • Barometric Pressure
  • Boundary Layer
  • Dynamic Pressure
  • Fluid Mechanics
  • Measurement
  • Pressure Gages
  • Pressure Gradients
  • Pressure Measurement
  • Pressure Transducers
  • Short Takeoff Aircraft
  • Static Pressure
  • Three Dimensional
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.