Effects of Distributed Propulsion on Commuter Aircraft Longitudinal Static Stability and Control

This paper presents wind-tunnel results quantifying the impact of a leading-edge distributed high-lift propeller system on the longitudinal stability and control characteristics of a generic 19-seat commuter aircraft model. The experimental campaign extends previous power-off tests on the same configuration to powered conditions, measuring lift, drag, and pitching-moment coefficients versus angle of attack and thrust coefficient at take-off flap setting. Results show that distributed propulsion affects longitudinal stability and control depending on thrust level and tail configuration—conventional aft-tail or T-tail—highlighting effects that are overlooked in literature. Static margin can be reduced by 8% or increased up to 6%, whereas the elevator control power can be doubled. Implications for tail sizing, pitch trim, and take-off performance are discussed.