H.Arizono, D.Kwak, T.Nomura

DOI Number: N/A

Conference number: IFASD-2017-008

Studies of the subsonic wing geometry were performed using multidisciplinary design tools to reduce the fuel consumption on a mission flight of 120-pax JAXA technology reference aircraft named TRA2012A. Aerodynamics and wing structural weight were estimated to evaluate the fuel consumption on several load distributions and aspect ratios of the wing on the transonic cruise flight. The drag was obtained using the CFD analysis, and the wing structural weight was obtained by structural sizing process using the FEM analysis. The fuel consumption was estimated using the mission analysis tools included in the aircraft conceptual design phase. The results show that the wing weight is increased with increasing the wing aspect ratio and changing the load distribution from triangle shape to elliptic shape. Lower drag is obtained at higher AR and elliptic and nominal load distributions.

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In Categories: 1. IFASD 2017, 1.Events, Aeroelasticity in Conceptual Aircraft Design
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