Authors
Abdul Nassar, Rahul Tarale, Naji Nasar A
Conference
ASME International Mechanical Engineering Congress and Exposition India 2026
Abstract
Electric Ducted Fans (EDFs) are increasingly used in unmanned aerial vehicles, electric aircraft, distributed propulsion systems, and high-performance drones. By enclosing a high-speed rotor within a duct, EDFs deliver higher thrust density, improved safety, reduced noise potential, and enhanced aerodynamic control compared to open propellers. However, achieving high efficiency in compact configurations is challenging due to tip leakage losses, rotor–stator interactions, compressibility effects, and structural limitations. Successful EDF development therefore requires an integrated aerodynamic and mechanical design approach. Naji Nasar DESiM Innovations (OPC) Private Limited Bengaluru, India electric ducted fans (EDF) have attracted considerable attention due to their compact form factor, enhanced safety, and potential for improved thrust density compared to open propellers. The presence of a surrounding duct reduces tip vortex losses, enhances static thrust, and provides improved aerodynamic control authority, particularly in low-speed and vertical flight regimes [1–3]. Additionally, ducted configurations offer potential acoustic benefits and improved integration within airframes, making them attractive for next-generation electric aviation systems [4]. This study presents the clean-sheet design and optimization of an electric ducted fan developed to meet a specified thrust target using TurboTides® as the primary design platform. The process began with 1D mean-line analysis to define key aerodynamic parameters, followed by integrated rotor and stator geometry generation and 3D blade modelling. Iterative CFD-guided refinements improved efficiency while maintaining stable operation. A parallel structural assessment evaluated centrifugal stresses, vibratory characteristics using Campbell and SAFE diagrams, resonance margins, and fatigue life. This ensured mechanical integrity, resonance avoidance, and durability under operating conditions. The final design satisfies thrust, efficiency, and structural requirements, demonstrating a robust multidisciplinary workflow for high-performance EDF development applicable to a wide range of electric propulsion systems.
Presentation Details
Event: IMECE-INDIA2026
Presentation Date: September 03–05, 2026
Location: Chennai
Status: Published
