DESIGN PRINCIPLES FOR ELECTRIC AIRCRAFT

The present disclosure relates to an aircraft comprising: a fuselage and at least one wing arranged in a tube-and-wing design; a plurality of propulsors; and a primary energy source configured to power the propulsors, the primary energy source comprising rechargeable batteries. The aircraft has a maximum takeoff mass `MTOM' of at least 8,618 kg; and an electric range factor 'ERF' of at least 6.