Skin-Friction Measurements at Subsonic and Transonic Mach Numbers with Embedded-Wire Gages

Abstract

Embedded-wire skin-friction gages were tested in the Acoustic Research Tunnel (ART) and on a model in Tunnel 16T at AEDC. The range of Mach numbers and Reynolds numbers considered was typical of the conditions encountered in transonic wind tunnel testing. Data obtained by the embedded-wire technique agreed well with data from conventional methods of measuring skin friction when the gages were calibrated in situ. When the gages were calibrated and reinstalled at a later data, the calibration coefficients could not be corrected by simple techniques.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1981
Accession Number
ADA093722

Entities

People

  • D. W. Sinclair

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Data Acquisition
  • Fluid Dynamics
  • Fluid Mechanics
  • Friction
  • Heat Transfer
  • Mach Number
  • Measurement
  • Mechanics
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Skin Friction
  • Static Pressure
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.