Wind-Tunnel Investigation of Ailerons on a Low-Drag Airfoil. 3 - The Effect of Tabs

Abstract

An investigation was made of the effects of 0.30-aileron-chord tabs on an NACA 66,2-216 (a = 0.6) airfoil equipped with a 0.20-airfoil-chord plain sealed aileron. The aileron profiles considered consisted of one profile conforming to the normal NACA 66,2-216 (a = 0.6) ordinates and a profile consisting of straight-line surfaces from the trailing edge to the hinge-line ordinates of the aileron. Basic data are presented from which the effect of tabs can be calculated for specific cases. The data are sufficient for the solution of problems of fixed tabs with a differential linkage, as well as simple and spring-linked balancing tabs.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1944
Accession Number
ADA801564

Entities

People

  • Ralph W. Holtzclaw
  • Robert M. Crane

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Aeronautics
  • Airfoils
  • Aspect Ratio
  • Coefficients
  • Drag
  • Free Stream
  • Leading Edges
  • Low Drag
  • Low Drag Airfoils
  • Plastic Explosives
  • Pressure Distribution
  • Reynolds Number
  • Trailing Edges
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.