Through an adequate preliminary design and analysis, the aero-propulsive synergistic effects present in DEP aircraft can be exploited to increase the overall capacities and system efficiency. This paper is divided into two main sections. The first one examines the impact of aero-propulsive coupling on aircraft architecture when modified during the preliminary design. Specifically, the propeller’s potential to increase lift is investigated. A built-in aerodynamic module is proposed as an approach for this purpose, using the all-electric NASA X-57 experimental concept as the reference aircraft. The second section focuses on several single-point constrained multidisciplinary optimizations aimed at maximizing lift generated through the interaction, reducing the stall speed, and minimizing the required installed power. The developed aerodynamic database is implemented into a nonlinear flight dynamics model, enabling the aircraft to be trimmed at the resultant stall speed. The resultant optimized configurations are able to reduce the stall speed up to 3.2 %, or the power utilized by the HLPs up to 8.27 %, while maintaining the same wing loading and stall speed.