EFFECT OF A PROBE ON THE DRAG AND PRESSURE DISTRIBUTION OF A HEMISPHERICAL NOSE,

Abstract

Wind tunnel tests were conducted over a Mach number range of 1.50 to 2.25 at a Reynolds' number of approximately 500,000 per inch in order to determine the effect of an extended probe on the drag and pressure distribution of a hemispherical nose. The drag is reduced on the order of 25% to 40% by extending the probe to its optimum length, with the larger reductions occurring at higher Mach numbers. At angles of attack above 6 degrees the reduction in drag is negligible. The conical region of separated air formed on the probe acts as a solid body, generating shock waves and pressures which correspond closely to conical theory. Normal forces on the probe were also investigated and found to be small. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 03, 1954
Accession Number
AD0658157

Entities

People

  • Paul H. Jackson Jr

Organizations

  • General Dynamics

Tags

DTIC Thesaurus Topics

  • Bodies
  • Cooperation
  • Mach Number
  • Pressure Distribution
  • Shock
  • Shock Waves
  • Solid Bodies
  • Waves
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Nanoscale Plasmonic Nanotechnology
  • Structural Dynamics.