THE INFLUENCE OF SLIGHT LEADING-EDGE BLUNTNESS ON BOUNDARY-LAYER TRANSITION AT A MACH NUMBER OF EIGHT

Abstract

The influence of leading-edge geometry on boundary-layer transition on a hollow cylinder aligned with the flow was studied under hypersonic conditions with near adiabatic wall temperature. Effects on the Reynolds number of boundary-layer transition produced by varying free-stream unit Reynolds number and small degrees of leading-edge bluntness are shown to be qualitatively similar to results previously reported by the authors for Mach numbers of 3 to 5. There was a pronounced favorable effect associated with increases in both factors. Comparisons are made with the theoretical estimates of the influence of bluntness given by Moeckel. Although qualitative agreement with Moeckel's theory is noted, quantitative agreement is not shown and some doubt concerning the theory is expressed.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1964
Accession Number
AD0431533

Entities

People

  • J. Leith Potter
  • Jack D. Whitfield

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Agreements
  • Air Force
  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Flow
  • Fluid Dynamics
  • Free Stream
  • Gas Dynamics
  • Geometry
  • Instrumentation
  • Layers
  • Leading Edges
  • Mach Number
  • Reynolds Number
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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