A Wind Tunnel Study of the Effects of Trailing Edge Modifications on the Lift-Drag Ratio of a Circulation Controlled Airfoil

Abstract

Wind tunnel tests were conducted to determine the effects of trailing edge modifications on the lift-to-drag ratio of a circulation controlled airfoil. The model was a 20 percent thick, five percent cambered, elliptical airfoil. The airfoil was modified in aft contour, blowing slot position, and blowing angle. A 1.5 inch splitter plate was mounted at the 99 percent chord for all tests. The tests were run at a Reynolds Number, based on model chord, of 741,000, while the angle of attack and blowing rate were varied during each test sequence.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1975
Accession Number
ADA023356

Entities

People

  • Vayl S. Oxford

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Aircrafts
  • Boundary Layer
  • Data Reduction
  • Dynamic Pressure
  • Free Stream
  • Governments
  • High Lift
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Static Pressure
  • Trailing Edges
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Agricultural and Food sciences
  • Physics

Readers

  • Aerodynamics/Aeronautics.