Static Aero-Propulsion Experiment of an Electric Ducted Fan

Electric ducted fans are increasingly being applied in the aviation sector due to their advantages in compact size, low noise, and zero emissions when compared to conventional gas turbine engines. This paper presents a test system for an electric Ducted Propulsion Fan (eDPF) developed by the Aerospace Propulsion Systems group at the School of Mechanical Engineering, Hanoi University of Science and Technology, Vietnam. The core component of the experimental system is a 390 mm diameter eDPF, made of carbon fiber composite and driven by a BLDC electric motor located within the fan core. The eDPF is mounted on a test stand equipped with force sensors and an optical RPM sensor, which are connected to digital display gauges. The power supply consists of LiFePO₄ battery packs, with voltage and current monitored by multimeters and controlled via a potentiometer connected to an ESC module. This electric thruster was experimentally operated at rotational speeds ranging from 2000 rpm to 7000 rpm in order to establish the relationship between its electrical and aero-propulsion characteristics. Initially, the testing aimed to determine the operational thrust range of the eDPF. Subsequently, comparisons were made between the electrical and aero-propulsion performance, as well as dimensionless parameters—including power coefficient (CP), thrust coefficient (CT), and figure of merit (FM)—under two configurations: 8-pack and 9-pack battery setups. In addition, an acoustic test was performed to measure the sound pressure level (SPL) at a distance of 1.0 m. The experimental results provide insights and recommendations for operating the eDPF at different power levels to achieve optimal thrust efficiency.