The study aims to examine the wing, fuselage and tail design parameters of Airbus and Boeing aircraft and to reveal the design criteria for the sizing of large commercial jets. Tin the study, the design and sizing data of 11 Airbus models and 14 Boeing models were compiled. The number of abreast seats, maximum seats, fuselage length, fuselage width, fineness ratio, tail section length, cockpit length and cargo compartment length are the main parameters studied about the fuselage design. Wing area, wingspan, aspect ratio, mean aerodynamic chord (MAC), taper ratio, dihedral angle, quarter chord sweep angle, and winglet lengths are the main parameters studied about the wing design. The area, span, aspect ratio, taper ratio, and quarter chord sweep angle of vertical and horizontal tail are the main parameters studied about the tail design. As a result of the study, exceptional designs and average design criteria for Airbus and Boeing aircraft have been revealed with the help of charts presented. In addition, the obtained linear correlations reveal that the MAC has about 0.14 times the wingspan and about 1.168 times the average chord length.
The analyses above showed general trends and gave an overview of the whole design space. To get more insight, one specific hybrid electric design is selected to evaluate in more detail. A design with a supplied power ratio of 0.34, a range of 1528 km and a battery-specific energy of 1000 Wh/kg is chosen for a number of reasons. First of all, higher benefits are obtained for short-range missions and this particular range makes a clear comparison with the ATR-72-600 possible. Second, as all the analyses are based on relatively low fidelity methods, the chosen design should have a safe margin from the design limit. Third, many aspects besides the environmental benefits affect the feasibility of a design. Just to name one, the MTOM will affect the production cost of an aircraft. Thus, a low power split is representative of designs which are more feasible. On the other hand, a high power split is beneficial in terms of emissions. In order to balance these conflicting requirements, a supplied power ratio of 0.34 is chosen. A comparison between the selected design and the reference design (similar to the ATR-72-600) is presented in Table 3. 2b1af7f3a8