Effect of Mach Number on Position Error as Applied to a Pitot-Static Tube Located 0.55 Chord Ahead of an Airplane Wing

Abstract

The effect on static-pressure measurements of locating a pitot-static tube 0.55 chord ahead of an airfoil section has been investigated. The tests were conducted in the NACA 24-inch high-speed tunnel on airfoil sections of various thickness ratios over a large range of Mach number. The results show that for a wing having a thickness ratio of 0.15 the measured Mach number, determined from a pitot-static-tube reading, is approximately 0.01 too low at a stream Mach number of 0.4 and approximately 0.03 too low at a Mach number of 0.8.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1944
Accession Number
ADA801529

Entities

People

  • W. F. Lindsey

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aeronautical Laboratories
  • Aircrafts
  • Airplanes
  • Altitude
  • Calibration
  • Compressive Properties
  • Errors
  • Low Altitude
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Pressure Gages
  • Pressure Measurement
  • Static Pressure
  • Thickness

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.