Aerodynamic effect of turbo prop engine slipstream on aircraft tail assembly vibration

• Autorzy: Zalewski W. , Stalewski W.

Identyfikatory

DOI

10.5604/01.3001.0010.3225

• Języki publikacji: EN

Abstrakty

EN

The article presents a computational analysis of the effect of the turboprop engine slipstream on generation of aerodynamic forces induced vibrations of aircraft tail assembly (empennage). Working propellers exhaust system, engine nacelle, and wing-engine nacelle flow interference phenomenon can cause strong non-stationary disturbances behind the wing of the aircraft. These disturbances, propagating in the direction of the aircraft tail assembly, may be an important factor influencing the operation of the airplane flow control system and the source of aerodynamic forces generating vibrations of the entire plane structure. The article presents an example of analysis of this phenomenon for a light passenger-transport aircraft using advanced numerical models for simulation of the flow around the aircraft. In the computational model, Navier-Stokes flow equations were solved by finite volume method with the K-Omega SST turbulence model to calculate the turbulent kinetic energy distribution in the flow slipstream behind the airplane propulsion unit. The Ansys Fluent commercial solver was used to run analyses. To perform the simulation, high quality, dedicated conformal computational mesh, consisting of hexahedral and tetrahedral elements was prepared to evaluate the propagation of the flow disturbances with limited numerical dispersion effect. Mesh generation was conducted using Ansys ICEM CFD and Mesher software. Unsteady aerodynamic forces for horizontal and vertical tail-planes of the airplane were computed during simulations. Fourier analysis of the driven forces was performed, which resulted in finding the dominating vibration frequencies generated by the flow field around the tail assembly. The visualization of the flow field and the regions of the strong disturbances were presented. Results can be exploited in the pre-design process of aerodynamic configuration of multi-engine aircrafts.

Słowa kluczowe

EN

air transport; aerodynamic wake; nacelle; tail assembly; vibration

• 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: 363--367
• Opis fizyczny: Bibliogr. 8 poz., rys.

Twórcy

autor

Zalewski W.

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

autor

Stalewski W.

• Institute of Aviation Krakowska Av. 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] Hanzal, V., Aerodynamic optimization of engine nacelle shape, Czech Aerospace Proceedings, 2/2015.
• [3] https://pl.wikipedia.org/wiki/CASA_C-295#/media/File:20140628_CASA_C-295_Ma%C5% 82opolski_Piknik_Lotniczy_6987.jpg.
• [4] https://pl.wikipedia.org/wiki/Shorts_C-23_Sherpa#/media/File:C-23.jpg.
• [5] Stalewski, W., Design and Optimisation of Exhaust System of Light Turboprop Airplane, Journal of KONES, 2016.
• [6] Stundl, M., Extension of the Use of Composite Materials in the L410 Airplane, Czech Aerospace Proceedings, 2/2015.
• [7] Yoneta, R., Sasaki, D., Nakahashi. K., Aerodynamic Optimization of an Over-the-Wing-Nacell-Mount Configuration, 48th AIAA Aerospace 2010.
• [8] Zalewski, W., The impact of propeller on aerodynamics of aircraft, Journal of KONBiN, 2015.

Uwagi

PL

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