MEASUREMENT OF FLOW ANGULARITY AT SUPERSONIC AND HYPERSONIC SPEEDS WITH THE USE OF A CONICAL PROBE

Abstract

The characteristics of a 40 degrees half-angle cone for measuring flow angularity were determined experimentally. Tests were conducted at a Mach number of 21 in helium with check points at Mach number 3.55 in air for angles of pitch up to 5 degrees. The air tests confirmed theoretical indications of small or negligible Mach number and test-medium effects for the case of air and helium. The instrument is capable of measuring flow angularity at high Reynolds numbers and speeds greater than that necessary for shock attachment to within + or - 1/3-degrees. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1961
Accession Number
AD0263572

Entities

People

  • Frank E. Swalley

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Attachment
  • Fluid Dynamics
  • Fluid Mechanics
  • Joining
  • Mach Number
  • Measurement
  • Mechanics
  • Reynolds Number

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Plasma Physics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow