GF
G. Fernandes Lourenço
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This thesis presents a trim optimization methodology for aircraft featuring distributed electric propulsion (DEP) systems and horizontal thrust units (HTU). The Unifier C7A-HARW, a 19-passenger hybrid-electric commuter aircraft with 12 wing-mounted propellers and a tail-mounted HTU, serves as the reference configuration. Multiple trim solutions with different types of propulsion systems usage and performance indicators, such as maximum range, endurance or lift-to-drag ratio, are explored through optimization, revealing complex relationships between angle of attack, airspeed, flap deflection, ruddervator deflection, required aerodynamic power and electric power consumed in steady level flight. Some unexpected results demonstrate that maintaining a constant low angle of attack and gradually reducing flap deflection as airspeed increases is desirable for lowering aerodynamic power requirements in trim conditions and that the wing tip propeller has an important role under certain circumstances. Empirical correlations between power requirements, angle of attack, airspeed, flap and ruddervator deflections are established, providing insights into the performance characteristics of DEP aircraft configurations and enabling efficient trim performance predictions useful for conceptual design.
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This thesis presents a trim optimization methodology for aircraft featuring distributed electric propulsion (DEP) systems and horizontal thrust units (HTU). The Unifier C7A-HARW, a 19-passenger hybrid-electric commuter aircraft with 12 wing-mounted propellers and a tail-mounted HTU, serves as the reference configuration. Multiple trim solutions with different types of propulsion systems usage and performance indicators, such as maximum range, endurance or lift-to-drag ratio, are explored through optimization, revealing complex relationships between angle of attack, airspeed, flap deflection, ruddervator deflection, required aerodynamic power and electric power consumed in steady level flight. Some unexpected results demonstrate that maintaining a constant low angle of attack and gradually reducing flap deflection as airspeed increases is desirable for lowering aerodynamic power requirements in trim conditions and that the wing tip propeller has an important role under certain circumstances. Empirical correlations between power requirements, angle of attack, airspeed, flap and ruddervator deflections are established, providing insights into the performance characteristics of DEP aircraft configurations and enabling efficient trim performance predictions useful for conceptual design.