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Electric and hybrid-electric propulsion technologies in aviation are becoming more attractive for aviation stakeholders not only due to the resulting reduction or elimination of the dependency on oil, whose availability and price are uncertain, but also because they are more reliable and efficient than traditional internal combustion engines. Moreover, combined with distributed electric propulsion (DEP), these technologies have shown potential in significantly reducing civil aircraft community noise impact and contribute towards delivering the strict mid-to-long-term environmental goals set by organisations worldwide, such as ACARE and NASA. This paper examines the noise impact of a concept tube and wing aircraft that falls in the A320 category and features various DEP systems using different power supply units (turboshaft engines or batteries) and number of electric propulsors. Meanwhile, considerations required for the transition from conventional to electric propulsion are discussed. Estimated Noise-Power-Distance (NPD) curves and noise exposure contour maps are also presented. It is concluded that indeed, the propulsors’ number is a key parameter for optimising the environmental performance of DEP aircraft and hence maximising the noise benefits. Also, it is shown that based on the entry into service year (2035) technology, totally electric aircraft tend to have a larger noise footprint than aircraft using hybrid electric propulsion systems.

Preliminary Noise Assessment of Aircraft with Distributed Electric Propulsion