We have presented methods applied to aeromechanic scenarios at Eurocopter. The examples illustrate how CFD increasingly supports classical comprehensive code computations in an industrial environment. CFD based polar computation is already state-of-the-art and represents a significant step forward in the design process: Reliable polars are available in a very early phase of the design process, allowing for an extended potential for optimization in an early design phase. The computational effort of CFD is required only in a 'pre-processing' manner and not on a case to case basis. Once the polars have been computed comprehensive code studies can be performed without penalty of additional computational effort. The same holds if comprehensive code interference models are derived from or validated by CFD computations. The approach is not yet as well established as polar computation by CFD but it is increasingly applied to various scenarios. Rotor loose coupling between CFD and comprehensive codes has proven its capability to improve the prediction of blade aerodynamics and blade loads compared to stand-alone comprehensive code simulations at least for steady forward flight cases. Validation for highly loaded rotors is in progress. An improvement in loads prediction is expected here as well. Concerning rotor performance the coupled method tends to slightly overpredict rotor power due to fully turbulent conditions. The incorporation of transition - even if it is only prescribed transition - leads to a significant improvement (50% reduction of the overprediction). The above statements hold for standard forward flight cases. For highly loaded rotors, the power overprediction due to fully turbulent flow might be counterbalanced by an insufficient reproduction of the Dynamic Stall and the related power increase. A conclusion can be drawn only after thorough evaluation of the validation test case. Due to the fruitful cooperation with a research network significant progress is achieved in the coupled and trimmed CFD simulation of the complete helicopter. Coupling interfaces are being extended and will be harmonized into a common coupling framework. Complete helicopter trim is already operational with isolated rotor coupling to CFD. Complete surface based modelling of the helicopter in CFD is the next step in front of us. The improved reproduction of interactional aerodynamics will lead to an improved helicopter performance prediction capability which will bring further potential to the validation of BEM (Blade Element Model) and will define a new generation of helicopter prediction tools.


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    Title :

    Addressing today's aeromechanic questions by industrial answers


    Additional title:

    Addressierung heutiger aeromechanischer Fragen durch Industrieantworten


    Contributors:


    Publication date :

    2010


    Size :

    18 Seiten, 26 Bilder, 25 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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