Corrections to Single-Shielded Total Temperature Probes in Subsonic, Supersonic, and Hypersonic Flow

Abstract

A new total temperature measurement correction is developed for the single-shielded type of probe. This method is based on a detailed analysis of the coupled heat transfer-viscous flow region existing within the probe. The correction is valid for all flow-field conditions and requires probe calibration data only in the free stream where flow properties are known. Total temperature measurements on the windward ray of a 4-deg sharp cone at Mach 10 in AEDC Hypersonic Tunnel (C) are used in conjunction with corresponding theoretical predictions to substantiate the present analysis. The new approach appears to be a significant improvement over present methods.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1976
Accession Number
ADA032725

Entities

People

  • M. O. Varner

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Calibration
  • Engineering
  • Experimental Data
  • Field Conditions
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Mach Number
  • Mass Flow
  • Measurement
  • Measuring Instruments
  • Reynolds Number
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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