Analysis of wing-engine nacelle aerodynamic interference

• Autorzy: Zalewski W. , Stalewski W.

Identyfikatory

DOI

10.5604/01.3001.0010.3096

• Języki publikacji: EN

Abstrakty

EN

The article presents an analysis of the wing-engine nacelle flow interference phenomenon on the example of a light twin-engine commuter aircraft. The problems of propulsion system integration with the wing in airplanes are now frequently the subject of advanced optimization research performed by aircraft manufacturers. The shape of the engine nacelle and its connection with the wing determines the quality of the flow around the wing in that area. This is important for high-lift devices placed at the wing trailing edge behind engine nacelle used during the take-off and landing process. Additionally the flow is effected by the disturbances generated by working propellers, the presence of air inlets and an exhaust system of the engine. The article presents a process of numerical optimization of an engine nacelle rear part shape. The main goal of the process was to eliminate the flow disturbances caused by the engine nacelle-wing interference phenomenon. During analysis, the Adjoint Solver method was used to designate nacelle body areas where modification should have the most important impact on the flow quality. The results obtained from adjoint solver were used in the process of finding the optimum shape of the rear part of the nacelle using a parametric geometry generator powered by Ansys Design Modeler and PARADES software. Comparative computational analysis for selected geometries of the engine nacelle was performed using commercial Ansys Fluent solver. Ansys Fluent is an advanced computational solver based on the finite volume method for solving the Navier-Stokes flow equations. Several dozen of geometric shapes were analysed in the optimization process of the nacelle rear part. The final result was the shape of the engine nacelle with correct flow without separation and vortex structures. The article presents results of calculations and visualization of the flow pattern for analysed cases.

Słowa kluczowe

EN

air transport; nacelle-wing integration; flow separation; adjoint solver; parametric design

• 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. 3
• Strony: 339--344
• Opis fizyczny: Bibliogr. 6 poz., rys.

Twórcy

autor

Zalewski W.

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

autor

Stalewski W.

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

Bibliografia

• [1] Chudy, P., Filakovsky, K., Friedl, J., Aerodynamic Analysis of Turboprop Engine Air Intake, Acta Polytechnica, Vol. 44, No. 3, 2004.
• [2] Hanzal, V., Aerodynamic optimization of engine nacelle shape, Czech Aerospace Proceedings, 2, 2015.
• [3] https://en.wikipedia.org/wiki/Antonov_An-26#/media/File:An-26_Ni%C2%B5_Nishava_Serbien _Marko_Stojkovic_IMG_2634-1-2.jpg.
• [4] Rivore, V., Propulsion Integration Challenges, Lecture to DGLR, 2007.
• [5] Stalewski, W., Design and Optimisation of Exhaust System of Light Turboprop Airplane, Journal of KONES, 2016.
• [6] www.evektor.cz/cz/ev-55-outback.

Uwagi

PL

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