PRESSURE MEASUREMENTS ON FOUR CONE-CYLINDER-FLARE CONFIGURATIONS AT SUPERSONIC SPEEDS

Abstract

Pressure distribution data are presented for four cone-cylinder-flare configurations at Mach numbers of 1.75 to 4.5. The angle of attack range was from -4 to +12 degrees. Roll angles ranged from 0 to 180 degrees. The Reynolds number remained constant at approximately 450,000 per inch. The boundary layer was made turbulent with a grit ban. The basic pressure data are presented in tabular form with the test conditions printed on each table.

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Document Details

Document Type
Technical Report
Publication Date
Oct 20, 1969
Accession Number
AD0699359

Entities

People

  • James A. Humphrey
  • William D. Washington

Tags

Communities of Interest

  • C4I
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Cross Flow
  • Electric Vehicles
  • Flow
  • Flow Fields
  • Layers
  • Mach Number
  • Measurement
  • Nanofibers
  • Photographs
  • Plastic Explosives
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Test Methods
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Ballistic Missile Meteorology
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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