Experimental Investigation of the Hypersonic Flow Over a Six Finned Configuration.

Abstract

Experimental data of the flow field over a six-finned configuration are compared with computations from an inviscid Euler and a parabolized Navier-Stokes (PNS) code to assess their accuracy. The experiments were conducted with a smooth and a grooved cylinder in a hypersonic (M=6.5) wind tunnel. Surface oil flow patterns, surface pressures, local heat flux rates and flow field pitot surveys are presented. The PNS computations are in good agreement with the measurements in the viscid regions. However, significant differences are noted in the viscous regions possibly due to nose tip bluntness effects and the associated entropy layer. Keywords: Hypersonic, Aerodynamics, Fluid mechanics, Navier Stokes, Code validation, Finned configuration, Experiment.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1987
Accession Number
ADA190870

Entities

People

  • A. M. Agnone
  • K. S. Parmar
  • V. Zakkay

Organizations

  • New York University

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Bow Shock
  • Computational Fluid Dynamics
  • Cross Flow
  • Cylindrical Bodies
  • Experimental Data
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Scientists
  • Turbulent Mixing
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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