Aerodynamic characterization and flight dynamics assessment of a modified general aviation aircraft for electric propulsion integration

Abstract

The ongoing transition toward sustainable aviation has accelerated research efforts focused on hybrid-electric and fully electric aircraft concepts. While significant advances have been achieved in electric propulsion technologies, the integration of energy storage systems within conventional aircraft platforms remains a major engineering challenge due to their impact on aerodynamic performance, mass distribution, stability characteristics, and structural loading conditions. The present work investigates the aerodynamic and flight dynamic characteristics of a modified general aviation aircraft intended as a demonstrator platform for future electric propulsion integration. A representative low-wing general aviation aircraft was selected as the baseline configuration and subsequently modified through the incorporation of a ventral energy-storage container designed to accommodate battery systems. Aerodynamic analyses were conducted using the USAF Digital DATCOM methodology under representative cruise conditions. Lift, drag, and pitching moment coefficients were evaluated over a broad angle-of-attack range, while static and dynamic stability derivatives were determined to assess longitudinal and lateral-directional stability characteristics. A nonlinear six-degree-of-freedom flight dynamics model was subsequently developed to investigate aircraft responses to control surface and propulsion commands. Numerical simulations involving aileron, elevator, rudder, and differential propulsion inputs were performed in order to evaluate controllability, stability margins, and dynamic coupling effects. The obtained results demonstrate that the modified configuration preserves satisfactory aerodynamic efficiency and dynamic stability while exhibiting only a moderate increase in drag associated with the external energy-storage system. The investigated configuration therefore represents a viable candidate for future studies involving hybrid-electric and fully electric propulsion architectures. The present work establishes a preliminary framework for multidisciplinary investigations combining aerodynamics, structures, flight mechanics, and propulsion system integration.