Abstract
Based on the research background of advanced aerodynamic design technology of distributed hybrid elec⁃ tric propulsion aircraft，a loose coupling design method of rectangle ducted fan unit under engineering constraints is proposed for the propulsive/aerodynamic coupling problem of distributed propulsion wing. Through the coupling itera⁃ tion of the rotor blade design optimization module influenced by the duct wall and the duct wall design optimization module based on a given rotor blade momentum source model，the complexity of the design problem is effectively re⁃ duced，and the multi-objective design optimization considering both hovering and forward flight characteristics of the rectangle ducted fan unit is achieved for this complex，multi-parameter object. Finally，the effectiveness and feasibility of the present loose coupling design method are verified through wind tunnel tests including force and pressure measurements.
| Translated title of the contribution | Research and experimental validation of loose coupling design method for propulsion wing unit |
|---|---|
| Original language | Chinese (Traditional) |
| Article number | 131150 |
| Journal | Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica |
| Volume | 46 |
| Issue number | 9 |
| DOIs | |
| State | Published - 15 May 2025 |