Air traffic has been growing for many decades and will, in all likelihood, continue to do so for the coming decades as well. At the same time, fuel prices will continue to increase and make air travel more and more expensive. In order to limit the negative effects this growth in air traffic has on the environment, as well as to reduce the fuel costs, it is necessary to realise further fuel savings compared to the current generation of aircraft. And from an aerodynamic point of view this means reducing the airframe drag. Current long range aircraft travel in the transonic speed regime, where compressibility effects of the air in the form of shocks limit the aircraft performance. One way to increase the aircraft's efficiency during the transonic cruise could be to apply means of shock control in order to reduce the drag effect of the shock. Extensive research over the last two decades has shown that one potential candidate to achieve this is the so-called shock control bump. However, despite all the successful research and all the benefits this concept has to offer, the shock control bump has not yet been implemented in an industrial context. This may be partly due to the fact that previous research mostly focused on an adaptive implementation of the shock control bump to avoid detrimental effects at the bump's off-design condition. An active adaptation mechanism, though, would necessarily require complex and expensive additional systems which render the whole concept less attractive. In contrast to that, this work will show that a well designed non-adaptive shock control bump may offer an overall net benefit on a long range cruise mission. And avoiding the necessity of an adaptation mechanism could help to considerably reduce the implementation costs of such a device. Also, past work mostly focused on showing that the method does work for academic cases. But there was never really a recipe delivered how shock control bumps could be used in an industrial design process. The present work closes this gap by developing a set of general design guidelines for non-adaptive shock control bumps that allow to rapidly achieve designs of a good standard. This methodology is a first step towards an industrialisation of the concept and can be useful to realise a future fully integrated wing design in the presence of shock control bumps. The numerical simulations of shock control bumps in this work are supported by wind tunnel measurements. These experimental results are used to both validate the relatively new concept of three-dimensional shock control bumps on airfoils and wings as well as the numerical methods applied. The aim of this work is to bring the previous academic research on Shock control bumps closer to an industrial implementation. It sets out to show that shock control bumps are a viable concept for drag reduction on transonic transport aircraft and to enable the efficient incorporation of this concept into an integrated design process.


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    Titel :

    Shock control bumps on transonic transport aircraft


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2014


    Format / Umfang :

    167 Seiten, Bilder, Tabellen, 63 Quellen



    Medientyp :

    Hochschulschrift


    Format :

    Print


    Sprache :

    Englisch






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