İTÜ 150x150 mm trisonik rüzgar tüneli kalibrasyonu ve bazı deneyler
Başlık çevirisi mevcut değil.
- Tez No: 75188
- Danışmanlar: PROF. DR. ZEKİ ERİM
- Tez Türü: Yüksek Lisans
- Konular: Uçak Mühendisliği, Aircraft Engineering
- Anahtar Kelimeler: Belirtilmemiş.
- Yıl: 1998
- Dil: Türkçe
- Üniversite: İstanbul Teknik Üniversitesi
- Enstitü: Fen Bilimleri Enstitüsü
- Ana Bilim Dalı: Uçak Mühendisliği Ana Bilim Dalı
- Bilim Dalı: Belirtilmemiş.
- Sayfa Sayısı: 60
Özet
ÖZET Rüzgar tünelleri atmosfer içinde hareket eden uçak, helikopter, roket, mermi gibi uçan sistemlerle araba, otobüs ve raylı sistemler gibi karada hareket eden araçların deneysel olarak incelenmesine olanak sağlayan uçak mühendislerinin temel laboratuarlarıdır. Rüzgar tünelleri çalışma hızlarına göre düşük ses altı, yüksek ses altı, transonik, ses üstü ve hipersonik tüneller olarak sınıflandırılırlar. İTÜ 150x150 mm Trisonik Rüzgar Tüneli, iki değiştirilebilir kesiti sayesinde ses altı, transonik ve ses üstü hızlarda deneyler yapılmasına olanak tanıyan bir rüzgar tünelidir. Rüzgar tünellerinin kalibrasyonu yapılacak deneysel çalışmaların güvenilirliği açısından son derece önemlidir. Bu çalışmada ilk başta İTÜ Uçak ve Uzay Bilimleri Fakültesi Aerodinamik Laboratuarında bulunan 150x150 mm kesitli deney odasına sahip trisonik rüzgar tünelinin genel donanımı ve ölçüm sistemleri tanıtılmaktadır. İkinci aşamada rüzgar tünelinin kalibrasyonu için yapılan çalışmaların sonuçlan verilmektedir. Verilen sonuçlar bazen tünel performans büyüklükleri veya parametreleri ismiyle de tanımlanmaktadır. Tünel performans büyüklüklerinin tespiti için deney odasında statik basınç dağılımı ve toplam basınç değişimini içeren basınç ölçümleri, tünel hız ölçüm güvenilirliğinin tespiti için akım görünürlülüğü ve bir standart modele ait kuvvet ve moment ölçümleri yapılmıştır. Bu deneyler, İTÜ Trisonik Rüzgar Tünelinin performans parametreleri hakkında önemli bilgiler elde edilmesini ve yeni ölçüm sistemlerinin geliştirilmesi gerektiğinin anlaşılmasını sağlamıştır. Bu değerlendirme sonucunda İTÜ 150x150 mm Trisonik Rüzgar Tünelinin yüksek hızlarda bilimsel çalışmalara uygun olduğu sonucu elde edilmiştir. vi
Özet (Çeviri)
SUMMARY CALIBRATION OF ITU 150x150 mm TRISONIC WIND TUNNEL AND SOME EXPERIMENTS Wind tunnels are devices which provide an airstream flowing under controlled conditions so that items of interest to speeds as low subsonic wind tunnels (incompressible flow), high subsonic wind aeronautical engineers can be tested. Wind tunnels can be classified according to their operating tunnels (subsonic compressible flow), transonic wind tunnels, supersonic wind tunnels and hypersonic wind tunnels. İTÜ 150x150 mm Trisonic Wind Tunnel can operate at subsonic, transonic and supersonic speeds. Before carrying out experimental research, determining the characteristics and calibration of a wind tunnel is of vital importance. Wind tunnels having different operating speeds need different calibration techniques. Pope [1] has stated that the calibration of a supersonic wind tunnel includes determining the Mach number, flow angularity and turbulence level in the wind tunnel. Weinert [3] has shown how investigations of Mach number and flow-angle distributions at supersonic Mach numbers were carried out with pitot rakes and a combined calibration rake for measuring flow angularity in the test section of the high speed wind tunnel TVM 150 at the Aeronautical Institute of the Technical University of Darmstadt. Calibration and determining the performance of İTÜ 150x150 mm Trisonic Wind Tunnel is carried out according to what is indicated in Pope's book [1]. In this study, firstly İTÜ 150x150 mm Trisonic Wind Tunnel and measurement systems are introduced. Secondly the study based on the calibration works including flow visualization, pressure and especially force measurements carried out on the İTÜ 150x150 Trisonic Wind Tunnel are explained in detail. Force measurements are accepted as a separate methodology for the completion of wind tunnel calibration. Visualization experiments to obtain the flow speed and quality within the test chamber are also accepted as another method for the verification of the calibration. Pressure measurements, force measurements and flow visualization applications on standard models have shown the reliability of the measurement apparatus.İTÜ 150x150 mm TRISONIC WIND TUNNEL İTÜ 150x150 mm Trisonic Wind Tunnel-an intermittent blowdown wind tunnel with variable Mach number-is designed for investigations in the subsonic, transonic and supersonic flow ranges of Mach numbers from 0.3 to 4. It has two different test sections for different Mach ranges. The first test section is used for obtaining Mach numbers from 0.3 to 2.2 and the second one is used from 2.6 to 4 Mach number. The installation works as a high pressure storage plant in an intermittent manner. There are two pressure storage units each having a volume of 27m3. They are charged to a pressure of 40 bar by means of a compressor plant coupled with a air drying and filtration unit. During experiments the needed pressurised air is supplied to the stagnation chamber through a regulation valve. The regulation valve maintains a constant pressure inside of the stagnation chamber whereas the reservoir pressure varies during the test run. A schematic figure of the ÎTÜ 150x150 mm Trisonic Wind Tunnel is shown in Figure 1. MEASUREMENT SYSTEMS Measuring times are limited for blowdown tunnels, for this reason a highly qualified data processing and control unit is required. Test runs at the 150x150mm İTÜ Trisonic Wind Tunnel are computer controlled and measurements are obtained through a data acquisition system. Total pressure and total temperature in the settling chamber and static pressure at the upper test section wall are evaluated by means of transducers and thermocouples attached to the system via an AD/DA data acquisition unit. A scanning valve can be used to measure pressures from 48 channels. Wind Tunnel Balances Wind tunnel balances are used to measure forces and moments acting on a model directly. The main characteristic of wind tunnel balances is the number of measured components. Depending on the problem, this number can vary from 1 to 6 [5]. They can be classified according to their components, measuring system - mechanical or strain-gaged and location - inside the model or inside the support. Wind tunnel balances must be calibrated to obtain a calibration matrix before measuring forces and moments. Calibration is done by applying known loads in the direction of each component. By this way Kij calibration matrix coefficients are evaluated. Calibration matrix is used according to the following equation to obtain axial force, normal force and pitching moment when Vij voltage values are measured during experiments. vX N M K" Km K n K. K A three component sting type strain-gage electronic balance is used in İTÜ 150x150 mm Trisonic Wind Tunnel to measure lift, drag force and pitching moment at various angles of attack. CALIBRATION WORKS Calibration of the İTÜ Trisonic Wind Tunnel has been carried out in three steps : determination of total and static pressure distribution within the test chamber, determination of free stream Mach number by flow visualization method, force and moment measurements on standard models. Pressure Measurements Tracking a pitot tube and a static tube along a vertical section of the test chamber, total and static pressure distributions are evaluated in two different Mach numbers - M=2.67 and M=3.13 - having intervals of 20mm at 7 vertical stations. In Figure 5 the ratio of the difference between measured total pressure in one station and average value of the total pressures measured in different stations, and total pressure in the settling chamber is given. It is obtained that the total pressure distribution is satisfactory. In Figure 6 the same ratio is evaluated for static pressures. In addition, static pressures are measured both from the upper and lower walls of the 2.6
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