Validation of Low Fidelity Propeller-Wing Modeling Method at Low Reynolds Number

An introduction of slipstream effects induced by the distributed propeller at low Reynolds number will lead to notable reductions in aerodynamics efficiency with significance changes of the free-stream properties of the wing. To address the issues, a set of reasonable aerodynamic design method for multiple propeller-wing integration is necessary to capture the wing aerodynamics performances behaviour at low Reynolds number. In that respect, the flow condition of a rectangular wing with NACA0012 airfoil section under the influence of the propeller slipstream was simulated and validated using low-order fidelity solver. A validation of the methods chosen found to be assuring in comparison with experimental data. The effects of various parameters were taken into account like the angle of attack, the rotational speed, the thrust and the power required. The aerodynamic aspect of the propeller-wing integration for a number of actuator disks propeller modelled distributed along the span of the wing of the aircraft is measured. The results show the role of propeller diameter and the numbers installed along the wingspan lead to a significance increase on lift performance and lift to drag ratio.