Direct Measurements of Skin Friction in Supersonic Combustion Flow Fields

Abstract

The final report consists of an AIAA and an ASME paper. An experimental investigation was conducted to measure skin friction along the chamber walls of supersonic combustors. A direct force measurement device was used to simultaneously measure an axial and transverse component of the small tangential shear force passing over a non-intrusive floating element. Skin friction coefficients between 0.001-0.005 were measured dependent on the facility and measurement location . Analysis of the measurement uncertainties indicate an accuracy to within + or - 10-15% of the streamwise component.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1993
Accession Number
ADA262878

Entities

People

  • D. J. Deturris
  • J. A. Schetz
  • K. M. Chadwick
  • R. F. Hellbaum

Organizations

  • Virginia Tech

Tags

Communities of Interest

  • Sensors

DTIC Thesaurus Topics

  • Boundary Layer
  • Climate Change
  • Combustion
  • Combustors
  • Computational Fluid Dynamics
  • Heat Transfer
  • Mach Number
  • Measurement
  • Physics Laboratories
  • Skin Friction
  • Static Pressure
  • Supersonic Combustion
  • Temperature Gradients
  • Test Facilities
  • Three Dimensional
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Combustion and Flow Dynamics.
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow