Supersonic Wind Tunnel Tests on Four Wings with Sweepback

Abstract

Tests of four airfoils with sweepback angles of 0, 30, 60, 67.5 deg. at a Mach number of 1.72 are compared with a simple theory. It is shown that little improvement in the lift-drag ratio is produced until the airfoil lies inside the Mach angle, but that the L/D ratio may be almost doubled using the proper sweepback angle.

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Document Details

Document Type
Technical Report
Publication Date
Sep 24, 1945
Accession Number
AD0492603

Entities

People

  • Allen E. Puckett

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airfoils
  • Aspect Ratio
  • Drag
  • Flow
  • Free Stream
  • Friction
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Skin Friction
  • Supersonic Airfoils
  • Supersonic Wind Tunnels
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow