The Interaction of Boundary Layer and Compression Shock and its Effect Upon Airfoil Pressure Distributions

Abstract

Tests performed over range of Reynolds and Mach numbers show that apparently shockless pressure distributions observed experimentally at supercritical Mach can be accounted for by marked thickening of boundary layer over shorter chordwise extent. At Reynolds Number 1,500,000, aerodynamically clean or dirty surfaces do not materially affect drag at supercritical speeds.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1947
Accession Number
ADA800555

Entities

People

  • Gerald E. Nitzberg
  • H. J. Allen
  • Max. A. Hesslet

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aeronautics
  • Boundaries
  • Boundary Layer
  • Compression
  • Flow
  • Flow Fields
  • Fluid Mechanics
  • Layers
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Shock
  • Shock Waves
  • Turbulent Flow
  • Waves

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Mathematics or Statistics