Conceptual design-optimisation of a subsonic hydrogen-powered long-range blended-wing-body aircraft
Swapnil S. Jagtap, Peter Childs, Marc Stettler
Abstract
The adoption of liquid hydrogen (LH 2 ) holds promise for decarbonising long-range aviation. LH 2 aircraft could weigh less than Jet-A aircraft, thereby reducing the thrust requirement. However, the lower volumetric energy density of LH 2 can adversely impact the aerodynamic performance and energy consumption of tube-wing aircraft. In a first, this work conducts an energy performance modelling of a futuristic (2030+) LH 2 blended-wing-body (BWB) aircraft (301 passengers and 13,890 km) using conceptual aircraft design-optimisation approach employing weight-sizing methods, while considering the realistic gravimetric and volumetric energy density effects of LH 2 on aircraft design, and the resulting reduction in aircraft thrust requirement. This study shows that at the design point the futuristic LH 2 BWB aircraft reduces the specific energy consumption (SEC, MJ/tonne-km) by 51.7–53.5% and 7.3–10.8%, compared to (Jet-A) Boeing 777-200LR and Jet-A BWB, respectively. At the off-design points, this study shows that by increasing the load factor for a given range and/or increasing range for all load factor cases, the SEC (or energy efficiency) of this LH 2 BWB concept improves. The results of this work will inform future studies on use-phase emissions and contrails modelling, LH 2 aircraft operations for contrail reduction, estimation of operating costs, and lifecycle climate impacts. • Blended-wing-body (BWB) enables effective and efficient use of liquid hydrogen (LH 2 ). • 2030+ LH 2 BWB aircraft specific energy consumption (SEC) is 54% lesser than Boeing-777. • SEC of 2030+ LH 2 BWB aircraft is 11% lesser than 2030+ Jet-A BWB. • Increasing range improves the SEC of this LH 2 BWB aircraft. • Increasing range increases the efficiency of this LH 2 BWB aircraft than Jet-A BWB.