Open Access

ABSTRACT

Aerodynamic Analysis of Helicopter Rotor using a Time-Domain Panel Method

by Seawook Lee¹, Leesang Cho², Jin-Soo Cho³

1 Department of Mechanical Engineering, Hanyang University, Seoul, Korea. (Tel: +82-2-2220-1716; E-mail: mplsw@hanyang.ac.kr)
2 Department of Mechanical Engineering, Hanyang University, Seoul, Korea. (Tel: +82-2-2220-1716; E-mail: ppome815@hanyang.ac.kr)
3 School of Mechanical Engineering, Hanyang University, Seoul, Korea. (Tel: +82-2-2220-0429; E-mail: jscho@hanyang.ac.kr)

The International Conference on Computational & Experimental Engineering and Sciences 2008, 7(3), 113-122. https://doi.org/10.3970/icces.2008.007.113

Abstract

Computational methods based on the solution of the flow model are widely used for the analysis of low-speed, inviscid, attached-flow problems. Most of such methods are based on the implementation of the internal Dirichlet boundary condition. In this paper, the time-domain panel method uses the piecewise constant source and doublet singularities. The present method utilizes the time-stepping loop to simulate the unsteady motion of the rotary wing blade for the KHP. The wake geometry is calculated as part of the solution with no special treatment. To validate the results of aerodynamic characteristics, the typical blade was chosen such as, Caradonna-Tung blade and present results were compared with the experimental data and the other numerical results in the single blade condition and two blade condition. This isolated rotor blade model consisted of a two bladed rotor with untwisted, rectangular planform blade. Computed flow-field solutions were presented for various section of the blade in the hovering mode.

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Keywords

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