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Design and Analysis of the Control and Stability of a Blended Wing Body Aircraft

Future aircraft generations are required to provide higher performance and capacities with minimum cost and environmental impact. This calls for the design of revolutionary unconventional configurations, such as the Blended Wing Body (BWB), a new tailless aircraft which integrates the wing and the fuselage into a single lifting surface. It has been proven in previous works that this concept has an efficient economical performance and is a promising candidate for solving the current air traffic problems, despite its challenging control and stability features. KTH and DLR are investigating new ways to improve the aircraft conceptual design process in a multidisciplinary environment. The CEASIOM1 software for aircraft design is enhanced by implementing CPACS2, as an unified and more versatile software framework. After researching the latest developments in the BWB concept, a BWB aircraft baseline is designed and its aerodynamic behaviour and performance analyzed with a special emphasis on its stability and control features. The allocation and sizing of the control surfaces is then iterated over to find the optimum winglet size for minimum drag and radar detectability conditions. All in all, the satisfactory performance of the BWB concept and the usefulness of new design softwares were confirmed.

1 Computerised Environment for Aircraft Synthesis and Integrated Optimisation Methods
2 Common Parametric Aircraft Configuration Scheme

Some features of the software used during this study will be available in a next release of the CEASIOM package ...




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Created 2014-09-16 11:55:39

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