Flow-Field Study about a Hemisphere-Cylinder in the Transonic and Low Supersonic Mach Number Range

Abstract

A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range (M = 0.7 to 2.0). For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1975
Accession Number
ADA018157

Entities

People

  • T. Hsieh

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Bodies
  • Bodies Of Revolution
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Engineering
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Hemispheres
  • Mach Number
  • Method Of Characteristics
  • Pressure Distribution
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.
  • Electromagnetic Wave Scattering and Antenna Radiation Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow