Investigation of Wing Characteristics at a Mach Number of 1.53. 1 - Triangular Wings of Aspect Ratio 2

Abstract

As part of a general study of wing characteristics at supersonic speed, wind tunnel tests were conducted of three sharp-edge wing models having thickness ratio of 5% and a common triangular plan form of aspect ratio 2. The models were designed to study the effects of variation in thickness distribution and camber with the apex of the plan form both leading and trailing. Measurements were made of lift, drag, and pitching moment at a Mach number of 1.53 and a Reynolds number of 0.75 million. The experimental techniques are described and the measured data compared with the calculated results of the inviscid, linear theory.

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Document Details

Document Type
Technical Report
Publication Date
Dec 19, 1947
Accession Number
ADA800917

Entities

People

  • F. H. Matteson
  • J. N. Nielsen
  • W. G. Vincenti

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamics
  • Aeronautics
  • Airfoils
  • Aspect Ratio
  • Boundary Layer
  • Delta Wings
  • Flow
  • Fluid Dynamics
  • Geometry
  • Leading Edges
  • Mach Number
  • Measurement
  • Sweptforward Wings
  • Test Methods
  • Thickness
  • Triangles
  • Wind Tunnel Tests

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow