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G. Q. Zhang 1 and S. C. M. Yu 2 and A. Chien 3 and Y. Xu 4
Recommended by Indra Vir Singh
1, Aerospace Engineering Division, School of Mechanical and Aerospace Engineering, Nanyang Technological University, 639798, Singapore
2, Academic Division, Singapore Institute of Technology, 179104, Singapore
3, Division of Interventional Neuroradiology, Department of Radiological Sciences, University of California, Los Angeles, Los Angeles, CA 90095, USA
4, Aircraft Design Division, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
Received 28 April 2013; Revised 7 July 2013; Accepted 24 July 2013
This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
1. Introduction
Due to the high efficiency characteristics, the propeller is often used for the low-speed aircrafts, such as the straight-line aircrafts and short-range aircrafts. With the growth of the computing capability and update in the improvement of CFD methods, many researchers investigated the interference between propeller and fuselage numerically.
Strash and Lednicer [1] had conducted simulations to study the aerodynamic interferences between the propeller slipstream and fuselage. The corresponding results showed that the comparisons between computed and measured wing pressure data were good and the propeller thrust coefficient was within 12% of the experiment. Muller and Aschwanden [2] had conducted the wind tunnel tests to analyze the slip-flow effects of the rapid transit aircraft. During the tests they had developed a new type of engine system which can be successfully applied to the low-speed wind test. Boyle et al. [3] had investigated the aerodynamic characteristics of the propeller in the transonic and subsonic conditions, which was equipped with six blades. The flow field created by the propeller slipstream in the steady and unsteady flows had also been studied.
Gamble and Reeder [4] performed the static test and wind tunnel test, respectively, to study the interference characteristics between the propeller and wing. The results showed that between 12 and 18% of propeller thrust had been translated into airframe drag, with the largest percentage occurring for the wing placement closest to the propeller. In order to solve the unsteady flow problems of three-dimensional multichip blade in preflight...