Wind Tunnel Tests for a Pitot-Static Probe Designed To Measure Aircraft Speed and Altitude at Subsonic Compressible and Transonic Regimes

Authors

  • Hasan Tabanlı ROKETSAN Missiles Inc., Propulsion Systems Design Department
  • Kemal Bulent Yüceil İstanbul Technical University

Keywords:

Pitot-Static Probe, Wind Tunnel Test, Speed and Altitude Measurement

Abstract

A pitot-static probe to measure speed and altitude of aircrafts over a range of flight speeds from 0.5 to 0.95 Mach was designed by means of computational fluid dynamics (CFD) analyses and its tests carried out at ITU Trisonic Wind Tunnel. The goal of design studies is to achieve acceptable low error rates in both speed and altitude measurements. The purpose of the wind tunnel tests is to verify the results obtained from the CFD analyses and to determine the characteristics of the designed probe under real flow conditions. In this paper, the parameters used in the design and their effects on the measurement performance of the probe are discussed. In addition, wind tunnel testing methods applied to obtain the characteristics of the designed pitot-static probe with high accuracy are given in detail in this article.

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Published

30-07-2021

How to Cite

[1]
H. Tabanlı and K. B. Yüceil, “Wind Tunnel Tests for a Pitot-Static Probe Designed To Measure Aircraft Speed and Altitude at Subsonic Compressible and Transonic Regimes”, JAST, vol. 14, no. 2, pp. 145–153, Jul. 2021.

Issue

Vol. 14 No. 2 (2021)

Section

Articles

License

The manuscript with title and authors is being submitted for publication in Journal of Aeronautics and Space Technologies. This article or a major portion of it was not published, not accepted and not submitted for publication elsewhere. If accepted for publication, I hereby grant the unlimited and all copyright privileges to Journal of Aeronautics and Space Technologies.

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