Design and optimisation of main rotor for ultralight helicopter

• Autorzy: Stalewski W.

Identyfikatory

DOI

10.5604/01.3001.0010.3148

• Języki publikacji: EN

Abstrakty

EN

A modern main rotor, dedicated to the ultralight helicopter, has been designed and optimised. Due to assumed simplicity of the rotor design and taking into account some technological constraints, the principal purpose of the presented research was to design a dedicated airfoil which, when applied on the main-rotor blades, would influence satisfactory improvement in a performance of the ultralight helicopter, especially in fast flight. The design and optimisation process has been supported by a computational methodology. The in-house software has been used for direct and inverse design of shapes of the rotor-blade airfoils. Aerodynamic properties of the airfoils as well as the helicopter main rotor were evaluated based on both the two-dimensional and three-dimensional flow simulations conducted using the ANSYS FLUENT software that was used to solve U/RANS equations. Based on the results of conducted computational simulations of fast flight of the ultralight helicopter, it can be concluded that the newly designed main rotor, compared to the baseline, may give certain improvement in helicopter performance in fast flight. In addition, the application of this newly designed rotor may lead to increase of a maximum speed of the helicopter flight, due to the greater lift force achievable by this rotor on the retreating blade, which is favourable from point of view of keeping of a lateral balance of the helicopter in fast flight.

Słowa kluczowe

EN

rotorcraft; ultralight helicopter; main rotor; airfoil; computer-aided design; optimisation

• 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: 2017
• Tom: Vol. 24, No. 4
• Strony: 287--295
• Opis fizyczny: Bibliogr. 5 poz., rys.

Twórcy

autor

Stalewski W.

• Institute of Aviation Aerodynamic Department, Centre of New Technologies Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 532, fax: [phone]

Bibliografia

• [1] ANSYS FLUENT User’s Guide. Release 15.0, ANSYS, Inc., November 2013. Available from: http://www.ansys.com.
• [2] Drela, M., Youngren, H., Scherrer, M., Deperrois, A., available at: http://www.xflr5.com/ /xflr5.htm, 2012.
• [3] Leishman, J. G., Principles Of Helicopter Aerodynamics, Cambridge University Press, 2000.
• [4] Stalewski, W., Żółtak, J., Optimisation of the Helicopter Fuselage with Simulation of Main and Tail Rotor Influence, Proceedings of the 28th ICAS Congress of the International Council of the Aeronautical Sciences, ICAS, Brisbane, Australia, ICAS 2012 CD-ROM Proceedings, 23-28 September, 2012.
• [5] Stalewski, W., Kania, W., Development of New Generation Main and Tail Rotor Blade Airfoils, Proceedings of 22nd Congress of International Council of the Aeronautical Sciences, ICAS 2000 CD-ROM Proceedings, Harrogate, United Kingdom 27.08-01.09, 2000.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).