1. Lithium-Air Powered E-190 type aircraft By Michael Vegh 1

2. The Problem 2 Designs and optimizes the wing parameters, electric propulsion system, as well as the mission flight profile of a E-190 type aircraft, replacing the jet A and turbofan with lithium- air batteries (Esp=2000 W-h/kg, Psp=.64 kW/kg, est. 2030 timeframe), ducted fans, and electric motors. The aircraft carry the same number of passengers a specified distance, and uses the same tail as the E-190

3. Design Variables 5 climb segments with target altitudes as well as climb velocities (vertical climb rate was maintained as equal to the given E-190 values) Cruise velocity Wing sweep, twist at the root and tip, as well as reference area Li-Air battery energy Li-S battery energy and power 3

4. Constraints 4

5. Sample Results (3800 km range) 5

6. Sample Design Results 6

7. Sample Design Variables (3800 km) 7 ElectricE-190 Climb Alt1(km)2.144216573.048 Climb Alt 2 (km)5.582885813.657 Climb Alt 3 (km)5.658210257.62 Climb Alt 4 (km)5.751917439.7536 Climb Alt 5 (km)5.7749127611.2776 Vclimb1(m/s)138.90885138 Vclimb2(m/s)150.408709168 Vclimb3(m/s)225.516393200 Vclimb4(m/s)174.643398230 Vclimb5(m/s) 206.298598230 Vcruise(m/s)230 alpha_rc (degrees)2.966037522 alpha_tc (degrees)-4.989269210 wing sweep (degrees)8.79E-0522 Sref (m^2)114.19155492 cruise range3584.803253796.6