HEMISPHERE-CYLINDER PRESSURE DISTRIBUTIONS AT SUPERSONIC AND HYPERSONIC MACH NUMBERS

Abstract

Pressure distributions on a hemisphere-cylinder at a Mach number of 10 and at angles of attack up to 25 deg are presented. These experimental distributions are compared with hypersonic blunt-body analytical and numerical solutions. Experimental stagnation point velocity gradients, sonic point locations, and pressure drag coefficients for hemispheres at Mach numbers from 1.8 to 21 have been compiled, and empirical relations are developed for these parameters as functions of Mach number.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1966
Accession Number
AD0804001

Entities

People

  • E. L. Clark

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Blunt Bodies
  • Bodies
  • Boundary Layer
  • Coefficients
  • Contracts
  • Equations
  • Free Stream
  • Governments
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Stagnation Point
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow