Application of the modified blade element method for propeller blade design on high-speed helicopter X³

• Autorzy: Karczewski, M. , Eglin, P.
• Konferencja: International Symposium on Compressor & Turbine Flow Systems Theory & Application Areas "SYMKOM" (11 ; 20-23.10.2014 ; Łódź, Polska)
• Języki publikacji: EN

Abstrakty

EN

The X³ helicopter is the experimental demonstrator of the H3 compound helicopter concept (High speed Hybrid Helicopter) developed by Airbus Helicopter and intended to operate at cruise speeds of about 113 m/s (220 kt). It is equipped with short fixed wings and two side-mounted propellers. Usually, fixed-wing propellers are sized to optimize the power consumption in cruise flight. In the case of a compound helicopter, some other flight cases such as hover and descent in autorotation also have to be considered. The geometrical criteria to satisfy all flight regimes may be contradicting what implies a compromise and a new approach to the propeller design. This paper presents the different steps of X³ propellers design from novelty theoretical Blade Element Method studies confirmed by CFD, experimental and flight tests.

Słowa kluczowe

PL

helikopter; eksperyment; lot próbny

EN

high-speed helicopter; compound helicopter; BEM; CFD; experiment; flight test

• Czasopismo: Zeszyty Naukowe. Cieplne Maszyny Przepływowe - Turbomachinery / Politechnika Łódzka
• Rocznik: 2014
• Tom: nr 145
• Strony: 63--64
• Opis fizyczny: Bibliogr. 4 poz.

Twórcy

autor

Karczewski, M.

• Institute of Turbomachinery Lodz University of Technology 219/223 Wolczanska St, 90-924 Lodz, Poland,

autor

Eglin, P.

• Airbus Helicopters Aéroport International Marseille Provence 13725 Marignane Cedex, FRANCE

Bibliografia

• [1] Adkins Ch.N. and Liebeck R.H.: Design of Optimum Propellers. Journal of Propulsion and Power 10, No. 5, Sept.-Oct. 1994, 676-682.
• [2] Karczewski M.: Optimization of Propeller Blade for Application on a Specialty Aircraft, PhD Thesis, Lodz University of Technology, Sept. 2011.
• [3] Leishman G.J.: Principles of helicopter aerodynamics. Cambridge University Press, Cambridge, UK, 2000.
• [4] Eglin, P.: Patent EP 2258615 A1 / US 20100312421 A1 – Flight control assistance device for a hybrid helicopter, 2010.