Abstract
The fluid-structure coupled and trimmed simulation of a helicopter rotor in forward flight is a computationally intensive task, hence it is a limiting factor for optimization studies of rotor blades. Therefore, the possibility of reducing the necessary trim iterations is investigated. Firstly, the quality criterion lift over drag is found to differ only slightly between a three and a four component trim while the three component trim requires less trim iterations. Secondly, the initial trim conditions for new blade shape geometries are predicted based on existing simulation results. For the present study a two dimensional parametric area resolved with 15 results is used for the interpolation of global quality criteria such as power and lift over drag as well as local properties such as the thrust distribution. The beneficial effect on the rotor trim using interpolated initial conditions is demonstrated.
The authors would like to thank the aerodynamic department of Eurocopter and the German Federal Ministry of Economy and Technology (BMWi) for its funding in the framework of FTEG-ECO-HC under grant 20H0803. We would also like to thank the members of the Helicopters and Aeroacoustics group at the IAG for their contribution.
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Hollands, M., Keßler, M., Krämer, E. (2014). Blade Shape Design: Trim Acceleration for Fluid-Structure Coupled Simulations of an Isolated Rotor in Forward Flight. In: Dillmann, A., Heller, G., Krämer, E., Kreplin, HP., Nitsche, W., Rist, U. (eds) New Results in Numerical and Experimental Fluid Mechanics IX. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 124. Springer, Cham. https://doi.org/10.1007/978-3-319-03158-3_25
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