Abstract
The air flow past a wind tunnel model of an Eurocopter BO-105 fuselage, main rotor and tail rotor configuration is simulated by solving the time dependent Navier-Stokes equations. The flow solver uses overlapping, block structured grids to discretize the computational domain. The simulation setup and the execution on a parallel NEC SX-6 vector computer are described. The numerical results are compared with unsteady pressure measurements on the fuselage and the blades. An overall good agreement is found. Differences between predicted and measured data on the main rotor and the tail rotor can be explained by blade elasticity effects and a different trim law respectively. The computational performance of the flow solver is analyzed for the NEC SX-6 and NEC SX-8 vector computer showing a good parallel performance. Modifications of the code structure resulted in a reduction of the execution time for the Chimera procedure by a factor of 6.6.
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Schwarz, T., Khier, W., Raddatz, J. (2006). Simulation of the Unsteady Flow Field Around a Complete Helicopter with a Structured RANS Solver. In: Resch, M., Bönisch, T., Benkert, K., Bez, W., Furui, T., Seo, Y. (eds) High Performance Computing on Vector Systems. Springer, Berlin, Heidelberg. https://doi.org/10.1007/3-540-35074-8_9
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DOI: https://doi.org/10.1007/3-540-35074-8_9
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