AN EMPIRICAL CORRELATION OF PRESSURE ON BLUNT-NOSED CYLINDRICAL AFTERBODIES AT HYPERSONIC MACH NUMBERS

Abstract

The study provided a readily solvable correlating equation that accurately predicts the pressure distribution over the afterbodies of various blunt-nosed cylinders at hypersonic Mach numbers. The correlating equation is developed from experimental pressure data on a cylinder with three nose shapes (hemisphere, flat-face, and rounded-shoulder flat-face) at free-stream Mach numbers of 6, 8, and 10. For blunt-nosed cylinders with nose drag coefficients from 0.89 to 1.72, the correlating equation is applicable over an extended experimental range of Mach number from 5.0 to 10.2 for local pressures greater than free-stream pressure. A good correlation is obtained with the method of characteristics solutions for Mach numbers from 5 to 100 for ten nose diameters along the body, but the applicability of the correlating equation beyond the experimental limits was not demonstrated.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1968
Accession Number
AD0669565

Entities

People

  • R. H. Eaves Jr.

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Afterbodies
  • Air Force
  • Blunt Bodies
  • Bodies
  • Bodies Of Revolution
  • Coefficients
  • Diameters
  • Engineering
  • Experimental Data
  • Flow
  • Free Stream
  • Geometry
  • Hemispheres
  • Mach Number
  • Method Of Characteristics
  • Pressure Distribution
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Fluid Dynamics.

Technology Areas

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