Wind tunnel tests of the pusher propeller : an assessment of accuracy

• Autorzy: Ruchała P.

Identyfikatory

DOI

10.5604/12314005.1213740

• Języki publikacji: EN

Abstrakty

EN

A pusher propeller is one of popular types of the airplane propulsion. It is applied especially in light sport aircrafts and in the UAVs (Unmanned Aerial Vehicles). Its main advantage is that the engine with the pusher propeller does not affect the visibility from the cockpit and allows placing an electronic equipment in the front part of the UAV’s fuselage. The main disadvantage of the pusher propeller is that its performance may be worse than the tractor propeller, because of a stream distortion caused by the fuselage. It should be taken into account during propeller tests. The most accurate way is to investigate the pusher propeller in the presence of the complete airplane, as a part of airplane wind tunnel tests. However, this approach is possible in a late stage of the airplane design, when the geometry of the airplane is fixed. In the paper, an alternative, innovative approach for the propulsion tests has been presented. The propeller was investigated in a wind tunnel in a presence of the aft part of the fuselage, including a root part of the wing. A typical propeller and a ducted fan have been investigated. The results has been compared with the results of the wind tunnel tests of the complete airplane (with powered propulsion) to evaluate the accuracy of this methodology. The investigated propulsion was designed for a joined wing UAV, ILX-32 MOSUPS.

Słowa kluczowe

EN

air transport; air propulsion; wind tunnel tests; pusher propeller; ducted fan

• 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: 2016
• Tom: Vol. 23, No. 2
• Strony: 309--315
• Opis fizyczny: Bibliogr. 11 poz., rys.

Twórcy

autor

Ruchała P.

• Institute of Aviation, Department of Aerodynamics Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.:[phone]

Bibliografia

• [1] Bogdański, K., Krusz, W., Rodzewicz, M., Rutkowski, M., Design and optimization of low speed ducted fan for a new generation of joined wing aircraft, Proceedings of the 29th Congress of International Council of the Aeronautical Sciences, Sankt Petersburg 2014.
• [2] Bogdański, K., Rodzewicz, M., Miller, M., Ruchała, P., Koncepcja i realizacja badań zespołu napędowego w tunelu aerodynamicznym, Mechanika w Lotnictwie ML-XVI, pp. 123-134, Warszawa 2014.
• [3] Galiński, C., Hajduk, J., Kalinowski, M., Wichulski, M., Stefanek, Ł., Inverted Joined Wing Scaled Demonstrator Programme, Proceedings of the 29th Congress of International Council of the Aeronautical Sciences, Sankt Petersburg 2014.
• [4] Galiński, C., Hajduk, J., Assumptions of the Joined Wing Flying Model Programme, Prace Instytutu Lotnictwa, No. 1(238), pp. 7-21, Warszawa 2015.
• [5] Gudmundsson, S., General aviation aircraft design: Applied Methods and Procedures, Butterworth-Heinemann, Oxford 2013.
• [6] Lewandowski, R., Możliwości napędu śmigłami obudowanymi, Technika Lotnicza i Astronautyczna, No. 1/83, pp. 31-34, 1983.
• [7] Lis, M., Dziubiński, A., Galiński, C., Krysztofiak, G., Ruchała, P., Surmacz, K., Predicted Flight Characteristics of the Inverted Joined Wing Scaled Demonstrator, Proceedings of the 29th Congress of International Council of the Aeronautical Sciences, Sankt Petersburg 2014.
• [8] Roberts, S. C., The Marvel project part C: An investigation of the shrouded propeller propulsive system on the Marvelette aircraft, TRECOM-TR-64-41 (AD 608 187) (N65-13069), Mississippi State University/US Army Transportation Research Command, Fort Eustis 1964.
• [9] Ruchała, P., System pomiarowo-sterujący tunelu aerodynamicznego T-1, Prace Instytutu Lotnictwa, No. 5-6 (232-233), pp. 63-78, Warszawa 2013.
• [10] Wiśniowski, W., Specjalizacje Instytutu Lotnictwa - Przegląd i wnioski, Prace Instytutu Lotnictwa, No. 2(235) , pp. 7-16, Warszawa 2014.
• [11] Wiśniowski, W., XX lat Programu Samolotów Lekkich i Bezpieczeństwa, Prace Instytutu Lotnictwa, No. 3(236), pp. 7-25, Warszawa 2014. 315

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.