Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds

Abstract

Tests were conducted on wings having taper ratios from 0 to 1 mounted on rocket propelled test bodies to determine the effect of taper on the zero lift drag of wings at low supersonic speeds. Detailed data on models and test conditions are provided. comparison is made between results of theoretical drag calculations of tapered wings and applicable experimental values derived. Maximum thickness, leading edge, and trailing edge sweep are used in determining drag coefficient. At a constant leading edge sweep of 45 degree, no orderly variation of drag coefficient with taper ratio occurs.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1947
Accession Number
ADB813753

Entities

People

  • Robert L. Nelson
  • Sidney Alexander

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aircrafts
  • Airfoils
  • Aspect Ratio
  • Bodies
  • Coefficients
  • Drag
  • Free Stream
  • Leading Edges
  • Mach Number
  • Rocket Engines
  • Rockets
  • Test Vehicles
  • Thickness
  • Trailing Edges
  • Unmanned Aerial Vehicles
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow