STUDY OF THE BLUNT-BODY STAGNATION POINT VELOCITY GRADIENT IN HYPERSONIC FLOW

Abstract

Results of an experimental investigation to determine the stagnation point velocity gradients for a family of blunt axisymmetric shapes at hypersonic Mach numbers are presented. Data presented in the form of model pressure distributions and stagnation point Mach number gradients are compared with existing data and theories. Although not accurately predicting the results, Newtonian theory is shown to provide a good basis for data correlation. Variations in model pressure distribution and stagnation point Mach number gradient from free-stream Mach number 6 to 10 were small and essentially within experimental precision. Model bluntness ranged from a hemisphere-cylinder to a flat-nose-cylinder, and data were obtained at free-stream Mach numbers 6, 8, and 10 and a nominal Reynolds number of 1,000,000, based on model diameter.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1968
Accession Number
AD0669378

Entities

People

  • L. L. Trimmer

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Blunt Bodies
  • Bodies
  • Boundary Layer
  • Data Analysis
  • Diameters
  • Flow
  • Fluid Dynamics
  • Free Stream
  • Jet Propulsion
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Reynolds Number
  • Stagnation Point
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow