Wind tunnel tests of the Tu-154M aircraft aerodynamic characteristics

• Autorzy: Krzysiak Andrzej

Identyfikatory

DOI

10.2478/kones-2019-0064

• Języki publikacji: EN

Abstrakty

EN

Determination of possible manoeuvres to be performed by the aircraft requires knowledge of its aerodynamic characteristics including, in particular, characteristics of the aircraft at configuration with deflected control surfaces. In this article, the wind tunnel tests results of the model of passenger Tu-154M aircraft manufactured at the scale 1:40 are presented. The model was designed and manufactured by the Military University of Technology based on the Tu154M aircraft geometry obtained by full-scale object scanning. The model mapped all aircraft control surfaces, along with the gaps between these surfaces and the main wing part. During the tests all the model’s control surface like, flaps, ailerons, spoilers, slots, rudder, elevator and tail plane were deflected at the same deflection angles range as they are used in the full scale aircraft. The aerodynamic characteristics of the tested Tu-154M aircraft model were measured by the 6-component internal balance. Based on the obtained measurements the aircraft model aerodynamic coefficients were calculated. In the article the basic aerodynamic characteristics of the tested Tu-154M aircraft model i.e. lift, drag coefficients as well as pitching, yawing and rolling moment coefficients versus model angles of attack and sideslip angles were presented. The tests were performed in the Institute of Aviation low speed wind tunnels T-1 of the 1.5 m diameter test section at the undisturbed velocity, V∞ = 40 m/s

Słowa kluczowe

EN

applied aerodynamics; test reliability; aerodynamic measurements

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2019
• Tom: Vol. 26, No. 3
• Strony: 113--120
• Opis fizyczny: Bibliogr. 9 poz., rys.

Twórcy

autor

Krzysiak Andrzej

• Łukasiewicz Research Network – Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.:[phone], fax: [phone]

Bibliografia

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• [3] Olejnik, A., Kiszkowiak, Ł., Dziubiński, A., 16th Biennial International Conference on Engineering, Science, Construction and Operations in Challenging Environments, Cleveland 2018.
• [4] Wiśniowski, W., Polish Wind Tunnels on the Background of World Tunnels, Scientific Library of Institute of Aviation, 2016.
• [5] Pope, A., Rae, W., Low-Speed Wind Tunnel Testing, Wiley-Interscience Publication, 1984.
• [6] Mair, W., Gamble, H., The effect of model size on measurements in the R.A.E. high speed tunnel, Drag of two-dimensional symmetrical aerofoils at zero incidence, A.R.C.R. & M. No. 2527, 1944.
• [7] Tropea, C., Yarin, A., Foss, J., Handbook of Experimental Fluid Mechanics, Springer, 2007.
• [8] Steinle, F., Stanewsky, E., Wind Tunnel Flow Quality and Data Accuracy Requirements, AGARD Advisory Report, No. 184, 1982.
• [9] Krzysiak, A., Necessary Wind Tunnel Tests Conditions of Proper Two- and Three-Dimensional Measurements, Journal of KONES, Vol. 3, (25), pp. 315-322, 2018.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).