AN INEXPENSIVE SUPERSONIC WIND TUNNEL FOR HEAT-TRANSFER MEASUREMENTS. PART II. RESULTS FOR A LAMINAR BOUNDARY LAYER BASED ON A TWO-DIMENSIONAL FLOW MODEL FOR THE ENTRANCE REGION OF A TUBE

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1954
Accession Number
AD0045690

Entities

People

  • George A. Brown
  • Joseph Kaye

Organizations

  • Massachusetts Institute of Technology

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Aeronautical Laboratories
  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Equations
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laminar Boundary Layer
  • Mach Number
  • Mechanical Engineering
  • New York
  • Physics Laboratories
  • Pressure Gradients
  • Reynolds Number

Technology Areas

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