Endplate Effectiveness for a NACA 0015 Airfoil

Abstract

Lift and drag of a NACA 0015 airfoil fitted with five differently shaped endplates are measured at M= .114 and M=.15 while sweeping the angle of attack from -4 to 14 degrees at 2 degree increments. The triangular endplate performs well in enhancing lift, while reducing induced drag better than the other endplates. A scaled down version of the airfoil and endplates are run in a flow visualization water tunnel at 10 degrees angle of attack and 1 fps. The triangular endplate causes upwash aft of the airfoil, which cancels out some of the natural downwash due to angle of attack, thus decreasing drag.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1992
Accession Number
ADA373750

Entities

People

  • D. T. Williamson
  • R. I. Chaudhary

Organizations

  • United States Air Force Academy

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Airfoils
  • Coefficients
  • Data Acquisition
  • Department Of Defense
  • Directives
  • Flow
  • Flow Visualization
  • High Pressure
  • Mach Number
  • Reynolds Number
  • Subsonic Wind Tunnels
  • Technical Information Centers
  • Two Dimensional
  • Water Tunnels
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.