THE AERODYNAMIC CHARACTERISTICS OF A 75-DEG SWEPT DELTA WING AT HIGH ANGLES OF ATTACK AND MACH NUMBERS OF 2 TO 8 (U)

Abstract

An experimental investigation was conducted in a 12 in. supersonic tunnel and a 50 in. Mach 8 tunnel to determine the aerodynamic characteristics of a delta wing at high angles of attack. The configuration tested was a flat, blunt leading edge, delta wing with 75 degree sweepback. The tests were conducted at angles of attack from 30 to 105 degree and Mach numbers of 2, 3, 5, and 8. Longitudinal stability and drag characteristics, surface pressure distributions, and shock wave shapes are presented with theoretical estimates based on the Newtonian theory.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1962
Accession Number
AD0329345

Entities

People

  • C. J. Spurlin
  • E. L. Clark

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Air Force
  • Boundary Layer
  • Delta Wings
  • Gas Dynamics
  • Geometry
  • High Angles
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Shock Waves
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow