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

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.

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

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.

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[1] H. Pitot, "Description d'une machine pour mesurer la vitesse des eaux courantes et le sillage des vaisseaux," Mémoires de L'Académie, 1732.
[2] Anderson Jr, J. D., Fundamentals of Aerodynamics. McGraw-Hill Education, 2001, pp. 465-498
[3] W. M. White, "The Pitot Tube: Its Formula," Journal Association Engineering Socs., vol. 27, pp. 34- 77, 1901.
[4] A. Zahm, "Measurement of air velocity and pressure," Physical Review (Series I), vol. 17, p. 410, December 1903.
[5] W. B. Gregory, "The Pitot Tube," ASME, vol. 25, pp. 184-212, 1904.
[6] A. E. Guy, "Origin and Theory of the Pitot Tube," Engineering News, vol. 69, pp. 782-783, 1913.
[7] W. C. Rowse, "Pitot Tubes for Gas Measurements," ASME, vol. 35, pp. 633-691, 1913.
[8] B. F. Groat, "Pitot-Tube Formulas," Proc. Engrs. Soc. West. Penn., vol. 30, pp. 324-381, 1914.
[9] H. Kumbruch, "Pitot-Static Tubes for Determining The Velocity of Air," TM 303, 1925. [Online]. Available:http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020].
[10] K. G. Merriam and E. R. Spaulding, "Comparative Tests of Pitot-Static Tubes," National Advisory Committee for Aeronautics, TN 546, 1935. [Online]. Available: http://naca.central.cranfield.ac.uk/ [Accessed: Aug. 17, 2020]
[11] G. Kiel, "Total-Head Heter With Small Sensitivity to Yaw," National Advisory Committee for Aeronautics, TM 775, 1935. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[12] R. V. Hensley, "Calibrations of Pitot-Static Tubes at High Speeds," National Advisory Committee for Aeronautics, WR L-396, 1942. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[13] R. E. Rayle, An Investigation of The Influence of Orifice Geometry on Static Pressure Measurements. Massachusetts Institute of Technology, 1949.
[14] L. E. Hasel and D. E. Coletti, "Investigation of Two Pitot-Static Tubes at Supersonic Speeds," National Advisory Committee for Aeronautics, RM L8I02, 1948. [Online]. Available:http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[15] H. C. Mcclanahan Jr, "Wing-Flow Investigation of a 45 Degrees Cone as an Angle-of Attack Measuring Device at Transonic Speeds," National Advisory Committee for Aeronautics, RM L51E16, 1951. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[16] W. Gracey, W. Letko, and W. R. Russell, "Wind- Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack - Subsonic Speeds," National Advisory Committee for Aeronautics, TN 2531, 1951. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[17] W. Gracey, D. E. Coletti, and W. R. Russell, "Wind-Tunnel Investigation of a Number of Total- Pressure Tubes at High Angles of Attack - Supersonic Speeds," National Advisory Committee for Aeronautics, TN2261, 1951. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[18] W. R. Russell, W. Gracey, W. Letko, and P. G. Fournier, "Wind-Tunnel Investigation of Six Shielded Total-Pressure Tubes at High Angles of Attack - Subsonic Speeds," National Advisory Committee for Aeronautics, TN 2530, 1951. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[19] W. Gracey, A. O. Pearson, and W. R. Russell, "Wind Tunnel Investigation of a Shielded Total- Pressure Tube at Transonic Speeds," National Advisory Committee for Aeronautics, RM L5IKI9, 1952. [Online]. Available: http://naca.central.cranfield.ac.uk/ [Accessed: Aug. 17, 2020]
[20] W. R. Russell and W. Gracey, "Wind Tunnel Investigation of a Shielded Total-Pressure Tube at a Mach Number of 1.61," National Advisory Committee for Aeronautics, ILM L53L23a, 1954. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[21] W. Gracey, "Wind-Tunnel Investigation of a Number of Total-Pressure Tubes at High Angles of Attack-Subsonic, Transonic, and Supersonic Speeds," National Advisory Committee for Aeronautics, Hampton, VA, USA, Tech. Rep. NACA-TN-3641, 1956.
[22] W. Gracey and E. F. Scheithauer, "Flight Investigation at Large Angles of Attack of the Static- Pressure Errors of a Service Pitot-Static Tube Having a Modified Orifice Configuration," National Advisory Committee for Aeronautics, TN 3159, 1954. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[23] T. J. Larson, W. H. Stillwell, and K. H. Armistead, "StaticPpressure Error Calibrations for Nose-Boom Airspeed Installations of 17 Airplanes," National Advisory Committee for Aeronautics, RM H57A02, 1957. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[24] F. J. Centolanzi, "Characteristics of a 40º Cone for Measuring Mach Number, Total Pressure, and Flow Angles at Supersonic Speeds," National Advisory Committee for Aeronautics, TN 3967, 1957. [Online]. Available: http://naca.central.cranfield.ac.uk [Accessed: Aug. 17, 2020]
[25] N. R. Richardson and A. O. Pearson, "Wind- Tunnel Calibrations of a Combined Pitot-Static Tube, Vane-Type Flow-Direction Transmitter, and Stagnation-Temperature Element at Mach Numbers From 0.60 to 2.87," National Aeronautics and Space Administration, TN D-122, 1959. [Online]. Available: https://ntrs.nasa.gov/ [Accessed: Aug. 17, 2020]
[26] J. J. Horvath, R. W. Simmons, and L. H. Brace, "Theory and Implementation of The Pito-Static Technique for Upper Atmospheric Measurements," The University of Michigan, Ann Arbor, Michigan Tech. Rep. NS-1, 1962.
[27] T. J. Larson and L. D. Webb, "Calibrations And Comparisons of Pressure-Type Airspeed-Altitude Systems of The X-15 Airplane From Subsonic to High Supersonic Speeds," National Aeronautics And Space Administration, D-1724, 1963. [Online]. Available: https://ntrs.nasa.gov/ [Accessed: Aug. 17, 2020]
[28] L. D. Webb and H. P. Washington, "Flight Calibration of Compensated and Uncompensated Pitot- Static Airspeed Probes and Application of the Probes to Supersonic Cruise Vehicles," National Aeronautics And Space Administration, TN D-6827, 1972. [Online]. Available: https://ntrs.nasa.gov/ [Accessed: Aug. 17, 2020]
[29] H. Becker and A. Brown, "Response of Pitot Probes in Turbulent Streams," Journal of Fluid Mechanics, vol. 62, pp. 85-114, 1974.
[30] T. Christiansen and P. Bradshaw, "Effect of Turbulence on Pressure Probes," Journal of Physics E: Scientific Instruments, vol. 14, p. 992, 1981.
[31] W. B. Stephenson, "Use of The Pitot Tube in Very Low Density Flows," Arnold Engineering Development Center UNC10965-PDC, 1981.
[32] S. H. Cho and H. A. Becker, "Response of Static Pressure Probes in Turbulent Streams," Experiments in Fluids, vol. 3, pp. 93-102, March 1985.
[33] B. Chebbi and S. Tavoularis, "Pitot–Static Tube Response at Very Low Reynolds Numbers," Physics of Fluids A: Fluid Dynamics, vol. 3, pp. 481-483, March 1991.
[34] H. J. Humm, C. R. Gossweiler, and G. Gyarmathy, "On Fast-Response Probes: Part 2—Aerodynamic Probe Design Studies," in ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition, The Hague, Netherlands, June 13-16, 1994, pp. V005T15A004-V005T15A004.
[35] K. R. Raju, P. Porey, and G. Asawa, "Displacement Effect in Pitot Tube Measurements in Shear Flows," Journal of Wind Engineering and Industrial Aerodynamics, vol. 66, pp. 95-105, February 1997.
[36] M. Wysocki and S. Drobniak, "A Comparative Analysis of Correction Method for Total-Head Probes in Large Velocity-Gradient Flows," Journal of Wind Engineering and Industrial Aerodynamics, vol. 89, pp. 31-43, January 2001.
[37] A. R. Porro, "Pressure Probe Designs for Dynamic Pressure Measurements in a Supersonic Flow Field," in 19th International Congress on, ICIASF 2001, Cleveland, OH, USA, August 27-30, 2001, pp. 417-426.
[38] S. G. Etemad, J. Thibault, and S. Hashemabadi, "Calculation of the Pitot Tube Correction Factor for Newtonian and Non-Newtonian Fluids," ISA Transactions, vol. 42, pp. 505-512, October 2003.
[39] K.J. Masud, A. Latif, S. Sheikh, and K. Parvez, "Robust Design of an Aerodynamic Compensation Pitot-Static Tube for Supersonic Aircraft," Journal of Aircraft, vol. 44, pp. 163-169, January 2007.
[40] M. Kabaciński and J. Pospolita, "Numerical and Experimental Rresearch on New Cross-Sections of Averaging Pitot Tubes," Flow Measurement and Instrumentation, vol. 19, pp. 17-27, March 2008.
[41] D. Węcel, T. Chmielniak, and J. Kotowicz, "Experimental And Numerical Investigations of the Averaging Pitot Tube and Analysis of Installation Effects on the Flow Coefficient," Flow Measurement and Instrumentation, vol. 19, pp. 301-306, October 2008.
[42] Z. Sun, Z. Li, and J. Zheng, "Influence of Improper Installation on Measurement Performance of Pitot Tube," in International Conference on Industrial Mechatronics and Automation, Chengdu, China, May 15-16, 2009