Investigation of Wing Characteristics at a Mach Number of 1.53. 2 - Swept Wings of Taper Ratio 0.5

Abstract

Three component tests were conducted at a Mach number of 1.53 of seven wings varying in angle of sweep from 60 degrees sweepforward to 60 degrees sweepback. The wings had a uniform isosceles-triangle section 5 percent thick and a common taper ratio of 0.5. The range of sweep angles provided both supersonic and subsonic leading and trailing edges at the test Mach number. Measurements were made of lift, drag, and pitching moment at a Reynolds number of 0.75 million. The experimental results are analyzed and compared with characteristics calculated by means of linear theory. The experimental values of the lift-curve slope were found to agree reasonably with the theory over the complete range of sweep angles.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1948
Accession Number
ADA800916

Entities

People

  • Frederick D. Matteson
  • Milton D. Van Dyke
  • Walter G. Vincenti

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Airfoils
  • Aspect Ratio
  • Boundary Layer
  • Delta Wings
  • Fluid Dynamics
  • Leading Edges
  • Lepidoptera
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Reynolds Number
  • Shock Waves
  • Swept Wings
  • Sweptforward Wings
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow