The Aerodynamic Lift Performance Analysis of Channel-Wing Design for STOL Aircraft

Abstract

The use of Short Take-Off and Landing (STOL) aircraft with anupwardly opening semi-cylindrical channel, known as a channel-wing, is one of the best candidates for short-haul flights. The channel-wing utilized the entrainment of airflow on the inside of the wing channel, enhancing the pressure difference on the wing surfaces, boosting the generation of lift. The present study is aiming to acquire the aerodynamic performance for a new design; the propulsion unit is position behind the wing. The analysis is done experimentally with a 3D-printed model. The aircraft wing model is constructed with NACA 4412 profile, a wingspan of 400 mm, and a U-shapechannel diameter of 68 mm. Tested in an open loop wind tunnel at speed of up to 22 m/s, and angle of attack of up to +20 degrees. The result shows the lift coefficient can reach beyond 3, higher than those obtained by the conventional wing design. Also, it can delay the wing stall; the lift can be maintained beyond which the usual state (angle of attack) where the typical wing begins to stall. Indeed, the new channel-wing design is a good option to be considered, offers higher lift, and rises with speed. It generates more lift than conventional aircraft equipped with modern high-lift systems and outperforms the existing traditional channel-wing design, which is advantageous for short-haul flight.