Tables of Inviscid Supersonic Flow About Circular Cones at Incidence Gamma = 1.4. Part 1

Abstract

The report provides tabulated results for the inviscid flow field about several circular cones at incidence to a uniform supersonic stream (gamma = 1.4). The three velocity components, pressure and density are given at points between the circular cone and the corresponding attached bow shock wave. Also some overall quantities such as normal and axial force coefficients are listed. Results are given for Mach numbers ranging from 1.5 to 20, for cone half angles from 5 deg to 40 deg and for successive values of relative incidence 0, 0.1, 0.2 ......

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1969
Accession Number
AD0698779

Entities

People

  • D. J. Jones

Organizations

  • AGARD

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Bow Shock
  • Coefficients
  • Curve Fitting
  • Equations
  • Flow
  • Flow Fields
  • Inviscid Flow
  • Mach Number
  • Pressure Gradients
  • Shock
  • Shock Waves
  • Specific Heat
  • Supersonic Flow
  • Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Plasma Physics / Magnetohydrodynamics

Technology Areas

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