WIND-TUNNEL INVESTIGATION OF TURBULENT BOUNDARY LAYERS ON AXIALLY SYMMETRIC BODIES AT SUPERSONIC SPEEDS

Abstract

Characteristics of supersonic turbulent boundary layers were determined for regions of large pressure gradients - both favorable and adverse - and with and without heat transfer. Details of the velocity, temperature, and static-pressure profiles were measured at several stations on three bodies of revolution at Mach numbers from 1.61 to 4.50. Profile data are presented in both graphical and tabular forms. Integrated boundary-layer thicknesses - displacement, momentum, and energy - are presented. The measured growth of the boundary-layer thicknesses is compared with that predicted by two approximate theories.

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Document Details

Document Type
Technical Report
Publication Date
Feb 06, 1964
Accession Number
AD0435111

Entities

People

  • Darwin W. Clutter
  • Kalle Kaups

Organizations

  • Douglas

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Compressible Flow
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Incompressible Flow
  • Jet Propulsion
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Static Pressure
  • Test Facilities
  • Turbulent Flow
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

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