Computational model of high altitude aircraft aerodynamics

• Autorzy: Zalewski W.

Identyfikatory

DOI

10.5604/12314005.1213720

• Języki publikacji: EN

Abstrakty

EN

The paper presents computational fluid dynamics hybrid model for analysis of complex flow composed of flow zones at low Reynolds number and flow zones at relatively high Reynolds number conditions. In the described model both ranges of the flow are separated and resolved independently using different way of simulation. That kind of phenomenon is typical for aerodynamics of unmanned propeller driven aircrafts operating at very high altitude conditions (stratospheric). That type of aerial vehicles is now used for military and scientific purposes. In many cases, the wings of a plane are operating at relatively high Reynolds number flow conditions and low angles of attack while the parts of the propeller blades are working at low Reynolds number flow condition and high angles of attack. Described numerical model was used for analysis of the impact of working propellers on the aerodynamics of the aircraft. Analysis was made on the example of a twin-engine, unmanned aircraft with electric motors during the high altitude flight. Three configurations were studied and compared: the plane without propellers, the plane with pusher propellers and the plane with tractor propellers. For each configuration, distributions of aerodynamic coefficients along the span of the wing and their global values for the entire aircraft were estimated. Calculations were performed using the Fluent solver with implementation of a model of propeller based on the Blade Element Theory. Results of the analysis indicate a slight advantage of the tractor propellers configuration.

Słowa kluczowe

EN

transport; air transport; simulation; propeller-driven unmanned airplane; propeller-wing interaction; low Reynolds number flows

• 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. 1
• Strony: 437--444
• Opis fizyczny: Bibliogr. 9 poz., rys.

Twórcy

autor

Zalewski W.

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

Bibliografia

• [1] Adamski, M., Modelowanie i badania procesu sterowania bezzałogowymi statkami powietrznymi, Wydawnictwo Naukowe Instytutu Technologii Eksploatacji PIB, Radom 2016.
• [2] Catalano, F. M., On the Effects of an Installed Propeller Slipstream on Wing Aerodynamic Characteristics, Acta Polytechnica, Vol. 44, No. 3, 2004
• [3] Cichocka, E., Wyzwania i problemy w budowie stratosferycznych samolotów solarnych, Prace Instytutu Lotnictwa 221, Warszawa 2011.
• [4] Drela, M., XFOIL: An Analysis and Design System for Low Reynolds Number Airfoils, MIT Dept. of Aeronautics and Astronautics, Cambridge, Massachusetts 1990.
• [5] Gavin, K., Ananda, G. K., Deters, R.W., Selig, M. S., Propeller Induced Flow Effects on Wings at Low Reynolds Numbers, Fluid Dynamics and Co-located Conferences, 24-27 June, CA, 31st AIAA Applied Aerodynamics Conference, San Diego 2013.
• [6] Jankowski, A., Wybrane zagadnienia funkcjonalne i aplikacyjne ogniw paliwowych, Instytut Techniczny Wojsk Lotniczych, 2012.
• [7] Stalewski, W., Aerodynamic optymisation of joined-wing aeroplane, 6th Int. Conference on Experiments/Process/System Modelling/Simulation/Optimization 6th IC-EpsMsO, Athens 2015.
• [8] Stalewski, W., Numeryczna optymalizacja profili śmigłowcowych oparta na algorytmie genetycznym z uwzględnieniem kryteriów bazujących na niestacjonarnych charakterystykach aerodynamicznych, Prace Instytutu Lotnictwa, Nr 1-2, Warszawa 2006.
• [9] Stalewski, W., Parametric Modelling of Aerodynamic Objects – The Key to Successful Design and Optimisation, Aerotecnica Missili & Spazio, The Journal of Aerospace Science, Technology and Systems, Aerotecnica Vol. 91, No. 1/2, 2012.

Uwagi

PL

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