Numerical simulation of vortex ring state phenomenon for the Mi2 type helicopter tail rotor

• Autorzy: Zalewski W.

Identyfikatory

DOI

10.5604/12314005.1213772

• Języki publikacji: EN

Abstrakty

EN

The paper presents computational simulations of loss of helicopter tail rotor effectiveness (LTE) effect caused by rotor vortex ring state (VRS) phenomenon. The phenomenon is critical for safety of helicopter operations and it was an important factor in some military and civil helicopters serious accidents. Analysis was conducted on the example of the tail rotor of Mi2 and PZL Kania single main rotor medium helicopters, which are still in wide use in some parts of the world. That kind of dual blades tail rotor was designed with symmetrical NACA0012 airfoil. Full three-dimensional analysis of the flow around real geometry of the rotor blades was conducted by application of commercial solver Ansys Fluent. The simulation was made by resolving Unsteady Reynolds Averaged Navier Stokes equations by finite volume method with use of Moving Mesh and Moving Reference Frame techniques. A hover turn over a spot was chosen as flight condition of helicopter, which could induce the LTE phenomenon. Thrust and power consumption were estimated during computations. Visualization of the flow field and pathlines of the flow were presented for chosen stages of vortex ring formulation around the rotor. The sensitivity of dual blades tail rotors, which are popular in light and medium type of helicopters to LTE phenomenon, was estimated.

Słowa kluczowe

EN

air transport; helicopters; tail rotor VRS

• 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: 437--442
• Opis fizyczny: Bibliogr. 10 poz., rys.

Twórcy

autor

Zalewski W.

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

Bibliografia

• [1] Dziubiński, A., Stalewski, W., Vortex ring state simulation using actuator disc, Instytut Lotnictwa, Proceedings 21st European Conference on Modelling and Simulation, 2007.
• [2] Cuzieux, F., Basset, P.-M., Desoppe, A., Modeling of loss of tail rotor effectiveness conducting to unanticipated yaw, ICAS 2012, 28th International Congress of the Aeronautical Science, 2012.
• [3] Florczuk, W., Analiza powstawania pierścienia wirowego wokół wirnika głównego na podstawie badań śmigłowca W-3 Sokół przy użyciu pakietu obliczeniowego FLUENT, Prace Instytutu Lotnictwa, Nr 6 (201), Warszawa, 2009.
• [4] Grzegorczyk, K., Modelowanie lotu śmigłowca w warunkach występowania pierścienia wirowego za pomocą virtual blade model, Modelowanie Inżynierskie, Vol. 14, Nr 45, 2012.
• [5] http://barrieaircraft.com/photo/pzl-swidnik-mil-mi2-kania-02.html.
• [6] Kania, W., Stalewski, W., Development of new generation main and tail rotors blade airfoils, ICAS 2000 Congress, 2000.
• [7] Kania, W., Stalewski, W., Zwierchanowska, B., Design of the modern family of helicopter airfoils, Transactions of the Institute of Aviation, No. 191. Warsaw 2007.
• [8] Kania, W., Stalewski, W., Zwierchanowska, B., Inverse and direct optimistaion of tail rotor airfoil using genetic algorithm, Proceedings of the Forth International Seminar on RRDPAE'2000, Warszawa 2000.
• [9] Mil, M. L., Helicopters, Calculation and design, NASA, Washington, September 1967.
• [10] Prouty, R. W., A Possible Tail Rotor Problem, Vertiflight, January/February 2012.

Uwagi

PL

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