Langley Full-Scale-Tunnel Investigation of the Fuselage Boundary Layer on a Typical Fighter Airplane with a Single Liquid-Cooled Engine

Abstract

Investigations showed that for the range of angles of attack and boundary layer profiles at various fuselage stations the maximum displacement thickness was nearly 1.2 in and was at the most rearward station. The displacement thickness was found to be greatly affected by the pressure gradients over the windshield-canopy combination and in the wing-fuselage juncture. An average value for the shape parameter between 1.3 and 1.4 was obtained for the turbulent boundary layer.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1946
Accession Number
ADA801318

Entities

People

  • Jerome Pasamanick
  • K. R. Czarnecki

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Aircrafts
  • Airplanes
  • Boundaries
  • Boundary Layer
  • Displacement
  • Fighter Aircraft
  • Flow
  • Layers
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Static Pressure
  • Thickness
  • Turbulent Boundary Layer
  • Windshields

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.