Aerodynamic Design Trade Study and Optimization of a Blended Wing Body Airliner

Staub, Franco M.; Morita, Naoto; Entzinger, Jorg Onno; Tsuchiya, Takeshi

doi:10.2514/6.2019-3172

Cited by 2 publications

(1 citation statement)

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“…17,16,14,15,13 A common returning design choice for fixed-wing UAVs is the blended wing body (BWB): a more often than not tailless configuration with the fuselage, the aircraft's main body, integrated in the wing. 21,23,24,18,22,19,[25][26][27]20 The absence of a horizontal tailplane combined with profiles that have positive camber enforces the sweeping and twisting of the wing to obtain longitudinal static stability, the intrinsic desire of the airplane to correct minor changes in its angle of attack (α). 28,16,14,29 When swept backward, the sweeping of the wings introduces a pressure gradient on the wing normal to the free stream, decreasing from the root to the tip.…”

Section: Introductionmentioning

confidence: 99%

Design optimization-under-uncertainty of a forward swept wing unmanned aerial vehicle using SAMURAI

Wauters

2022

International Journal of Micro Air Vehicles

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In this paper the design optimization-under-uncertainty of a forward swept wing (FSW) blended wing body (BWB) unmanned aerial vehicle (UAV) is examined. Conventional BWBs are often tailless, which leads to a backward swept wing to ensure longitudinal static stability. This in turn can induce flow separation at the tip, leading to a loss of lift, controllability and the appearance of a nose-up pitching moment. A possible solution to this problem is a conceptual redesign by introducing a forward swept wing, which is inherently free of tip-stall, but needs a careful design in order to be controllable. However, fixed wing UAVs are often produced by means of direct injection expanded foam moulding, which is characterized by not negligible production tolerances. This lead to a reliability-based robust design optimization problem, for which a novel framework is employed: SAMURAI. Firstly, the method accounts for computational cost by means of surrogate modelling, an analytical treatment of the problem and an asynchronous updating scheme that balances design space exploration and objective exploitation. Secondly, the method treats the problem as a multi-objective problem, which leads to a Pareto front of robust and reliable designs. The result is a novel series of UAV designs that are inherently free of tip stall, perform robustly and meet the stability requirements with the target reliability obtained with a computationally feasible budget.

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