Experimental Investigation with a Distributed Propulsion Large-Scale Model Under Short Take-Off and Landing Conditions

This work investigated the complex propeller-wing interaction processes that arise from wings equipped with distributed electric propulsion systems and their acoustic consequences. The aeroacoustic tests were conducted in the DNW-NWB wind tunnel using a large-scale, two-element high-lift configuration wing model fitted with three co-rotating propellers, simulating the distributed propulsion system. The tests included various model configurations, changing the wing’s geometry and the operating conditions of the propellers. The geometric parameters included the separation distance between the propellers, their position relative to the wing, and the flap’s settings. The propellers’ operating conditions were designed to replicate flight conditions typical of climb and also short take-off and landing. This manuscript presents and discusses the experimental results from different configurations of the large-scale model under short take-off and landing conditions. Finally, it compares the results with previous findings obtained under climb flight conditions. This work was conducted within the framework of the Clean Sky 2 project DISPROP.