Flight Path and Wing Optimization of Lithium-Air Battery Powered Passenger Aircraft J. Michael Vegh * , Juan J. Alonso † Stanford University, Stanford, CA, 94305, U.S.A. Tarik H. Orra ‡ , Carlos R. Ilario da Silva § EMBRAER, S˜ao Jos´ e dos Campos, SP, 12277-901, Brazil. The design of electric-powered aircraft for use in the commercial aviation sector is a complex, heavily multidisciplinary problem that requires careful consideration of power and energy tradeoffs, in addition to more traditional performance metrics. A multidisciplinary, multifidelity aircraft design code called SUAVE (Stanford University Aerospace Vehicle Environment) has been developed in part to address these considerations. This paper explores the application of this design code towards a passenger aircraft at the commercial scale, with the wing, flight path, and an electric propulsion system designed and optimized for a prescribed number of passengers at a variety of different ranges. Additionally, aircraft weight sensitivities to battery technology, motor technology, as well as takeoff and landing constraints were evaluated, and their relative feasibility assessed. Nomenclature AoA angle of attack C C rate the battery is discharged at Esp specific energy f factor in empirical discharge loss F Faraday Constant G 0 Gibbs Free Energy h altitude I current P power P motor motor power Psp specific energy R effective resistance R 0 empirical resistance factor S ref wing reference area TOFL Take Off Field Length LFL Landing Field Length V velocity magnitude V 0 reaction potential x state of charge α twist Λ sweep * Ph.D. Candidate, Department of Aeronautics & Astronautics. † Associate Professor, Department of Aeronautics & Astronautics, AIAA Associate Fellow. ‡ Aircraft Conceptual Design Engineer - Embraer, AIAA Senior Member. § Technology Development Engineer - Embraer, AIAA Member. 1 of 13 American Institute of Aeronautics and Astronautics