The Blended Wing Body (BWB) aircraft is based on the flying wing concept. For this aircraft the literature has reported performance improvements compared to conventional aircraft. However, most BWB studies have focused on large aircraft and it is not sure whether the gains are the same for smaller aircraft. The main objective of this work is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a stable aircraft, with the analysis of static and dynamic stability. The design of BWB was carried out under the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). This design platform, suitable for conventional aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic analysis, performance and stability of the BWB aircraft.

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