Accession Number:

AD0658157

Title:

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

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS/POMONA CALIF

Personal Author(s):

Report Date:

1954-06-03

Pagination or Media Count:

32.0

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

Subject Categories:

  • Aerodynamics
  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE