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A Numerical Variational Approach for Rotor-Propeller Aerodynamics in Axial Flight

F. Simonetti1, R. M. Ardito Marretta2
Graduate Student, Department of Mechanics and Aeronautics, University of Palermo, Italy
Research Engineer, Department of Mechanics and Aeronautics, University of Palermo, Italy

Computer Modeling in Engineering & Sciences 2000, 1(3), 81-90. https://doi.org/10.3970/cmes.2000.001.383

Abstract

Advanced propellers are being developed to improve the performance and fuel economy of future transport aircraft. To study them, various aerodynamic prediction models and systems (from theory to experiment) have been developed via several approaches (Free Wake Analysis, helicoidal source methods, scale model tests). This study focuses on the development of an efficient numerical method to predict the behaviour of rotor or propeller in forward flight. Based on a variational approach, the present numerical technique allows a significant reduction of computer resources used in the calculation of instantaneous velocities to determine the wake geometry and the three-dimensional vortex flow streaming back from the propeller. Wind tunnel test data are presented to substantiate the theory and to show its limitations. The analytical structure of the model is described and its capability is analyzed by a numerical simulation checked against available with experimental data obtained on a scale model of a four-bladed propeller. Assuming the hypothesis of incompressible flow, the simulation results show a very good agreement with experiments for a wide range of operating parameters.

Keywords

variational numerical scheme, propeller wake

Cite This Article

Simonetti, F., M., R. (2000). A Numerical Variational Approach for Rotor-Propeller Aerodynamics in Axial Flight. CMES-Computer Modeling in Engineering & Sciences, 1(3), 81–90.



This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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