Thread by @temjinem

Title: Aerostructural Wing and Fuselage Optimization for Hydrogen-based Aircraft

Background: Currently, aviation is undergoing a large shift towards more sustainable, eco-friendly, and efficient aviation to meet the International Air Transport Association (IATA) ambitious

targets to mitigate CO2 emissions by 50% from air transport until 2050. Hydrogen technologies have emerged as a potential energy source represent a long-term option as a fuel for aviation. Beyond the purely technological issues, a holistic assessment requires looking at the

integration of hydrogen into the aircraft design towards hydrogen-powered aircraft. The development of the necessary systems to store and distribute hydrogen fuel on the aircraft for flight is a mandatory step toward such a system. Since liquid hydrogen cannot be reasonably

stored in the wings due to its volume, pressure, and the insulation required, new solutions must be introduced to integrate liquid hydrogen tanks into the fuselage. This opens up possibilities with regard to the design of the wing and the fuselage. The space in the wing reserved

previously for the fuel can now be used for optimizing the structural load paths for high aspect ratio wings incorporating natural laminar flow (NLF) or hybrid laminar flow control HLFC technologies for drag reduction. The shape of conventional transport aircraft is

tube-and-wing configuration (CTW), which remains up to today. For Hydrogen aircraft type (liquid H2 aircraft), it is most likely that the length and width of the fuselage will both increase to accommodate the integral LH2 tanks. The fuselage can generate up to 50% of total

profile drag (parasitic drag) for all-turbulent aircraft in cruise conditions. However, it is estimated that the contribution of the turbulent fuselage to airplane profile drag increases to more than 70% if the extended laminar regions on the wings and the tail surfaces are

obtained.

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