INVESTIGATION OF BOUNDARY-LAYER TRANSITION ON SWEPT WINGS AT MACH NUMBERS 2.5 TO 5

Abstract

Tests were conducted in the 12-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine boundary-layer transition locations on swept wings having a circular arc profile and modified arc profile. Test Mach numbers were from 2.5 to 5 over a Reynolds-number-per-inch range from 0.14 to 1. 08 million at sweep angles of 24, 36, and 50 deg for angles of attack of 0 and approximately -4 deg. Boundary-layer transition Reynolds numbers determined by a pitot probe, and results obtained visually with a sub limable solid are presented. The major factors influencing boundary-layer transition were wing sweep and model leading edge geometry. Increasing wing sweep and leading edge bluntness above a sweep angle of approximately 20 deg decreased the transition Reynolds number at all test Mach numbers.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1963
Accession Number
AD0410130

Entities

People

  • R. E. Brillhart
  • S. R. Pate

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Transition
  • Gas Dynamics
  • Geometry
  • Jet Propulsion
  • Layers
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Surface Temperature
  • Swept Wings
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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