SUPERSONIC WIND TUNNEL TESTS OF SMALL CALIBER PROJECTILES: CAL. .50 API M23; CAL. 60 API T39; AND 20mm HEI M97

Abstract

Three component tests of models of small caliber projectiles (Cal. . 50, Cal. .60, and 20mm) were conducted in the Aberdeen Wind Tunnels at a Mach Number of 1.72 to provide aerodynamic data at high angles of attack. These results are to be used for computing the forces and motion imparted to a projectile when fired from high-speed aircraft. All projectiles were aerodynamically unstable. The addition of rifling increased the fore drag coefficient with little effect on lift and moment curve slopes. The test results are presented in graphs of aerodynamic coefficients as a function of angles of attack.

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Document Details

Document Type
Technical Report
Publication Date
Jun 30, 1949
Accession Number
AD0693249

Entities

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Base Pressure
  • Boundaries
  • Boundary Layer
  • Coefficients
  • Diameters
  • Dynamic Pressure
  • High Angles
  • Layers
  • Mach Number
  • Measurement
  • Photographs
  • Projectiles
  • Static Pressure
  • Supersonic Wind Tunnels
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • ballistics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow