Experimental Pressure Distributions on Axisymmetric Forebodies at Mach 3 and Angles of Attack Up to 17.5 Degrees.

Abstract

Tabulations of experimental surface pressure distributions on both plunt and sharp axisymmetric forebodies are presented for a freestream Mach number of 3.0 and body angles of attack up to 17.5 degrees. The experimental details are described, but no analysis of the resultant data bas been undertaken. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1983
Accession Number
ADA140321

Entities

People

  • L. C. Ward

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Axisymmetric
  • Bodies
  • Boundary Layer
  • Boundary Layer Transition
  • Dynamic Pressure
  • Engineering
  • Fineness Ratio
  • Foreign Languages
  • Geometry
  • Instrumentation
  • Law
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Stagnation Pressure
  • Transducers
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.