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Journals / Havacılık ve Uzay Teknolojileri Dergisi / 2021 / Cilt: 14 - Sayı: 2

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

Hava Aracı Hızını ve İrtifasını Sıkıştırılabilir Ses-Altı ve Transonik Rejimlerde Ölçmek İçin Tasarlanmış Bir Pitot-Statik Probun Rüzgar Tüneli Testleri

Hasan TABANLI
Kemal Bülent YÜCEİL
Pages
145–153
Publication Date
2022-10-18
DOI
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AI Summary & Key Takeaways

AI Insight
⚡ TL;DR(Too Long; Didn't Read)

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.

📌 3 Key Takeaways

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Objective & Hypothesis: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 were carried out at ITU Trisonic Wind Tunnel.
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Key Findings & Data:The goal of the design studies is to achieve acceptable low error rates in both speed and altitude measurements.
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Conclusion & Impact: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.
🔬Design:Research Article
📍Scope:Comprehensive Sample
⚙️Variables:Domain Parameters

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 were carried out at ITU Trisonic Wind Tunnel. The goal of the 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.

Özet

0,5 ile 0,95 Mach aralığında uçuş hızına sahip hava taşıtlarında kullanılabilecek bir pitot-statik prob hız ve yükseklik ölçüm sisteminin tasarımı, hesaplamalı akışkanlar dinamiği (HAD) analizleri ve İTÜ Trisonik Rüzgar Tüneli’nde yapılan testler ile gerçekleştirildi. Tasarım çalışmalarının hedefi, hem hız hem de yükseklik ölçümlerinde, kabul edilebilir, düşük hata seviyelerine ulaşabilmektir. Rüzgar tüneli akış testlerinin amacı HAD analizlerinden elde edilen sonuçların doğrulanması ve tasarlanan probun gerçek akış şartları altındaki davranışının tespit edilmesidir. Bu çalışmada tasarımda kullanılan önemli parametreler ve bu parametrelerin ölçüm performansına etkileri tartışılmıştır. Ayrıca tasarlanan pitot-statik probun özelliklerinin yüksek doğrulukta elde edilmesi için uygulanan rüzgar tüneli test yöntemleri bu çalışmada detaylı olarak verilmektedir.

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Cite This Article

TABANLI, H., YÜCEİL, K. B. (2022). Wind Tunnel Tests for a Pitot-Static Probe Designed to Measure Aircraft Speed and Altitude at Subsonic Compressible and Transonic Regimes. Havacılık ve Uzay Teknolojileri Dergisi, Cilt: 14 - Sayı: 2, 145–153. https://ajindex.com/articles/535168

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References (10)

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