Study of Laminar Flow Control Aerofoil with Thrust Generator

Abstract

Present study is to make the laminar flow over the aerofoils usingsuction and to utilizing suctioned air as the input to the thrust generator. An aerofoil model is fabricated for experimental study in the wind tunnel. The aerofoil model fabricated has perforation in the leading edge up to quarter chord on the upper surface such that the suction is made at the first quarter surface over the aerofoil with an optimum suction rate obtained through CFD analysis. The lift and drag characteristics are studied for the aerofoil profile with and without suction. The flow separation is visualized by tuft technique. The suction air employed for generating thrust through a thrust generator which is capable of producing thrust through entrainment and inducement of air. The data obtained from the experiments the results of the aerodynamic performance with and without suction are obtained. This result is also compared with the CFD results. For CFD analysis an aerofoil model was created using the CATIA and imported to ANSYS CFX. From the experimental data obtained with and without suction, the changes in the aerodynamic efficiency are found. The range under which the Laminar flow control is more efficient has been identified. The mechanism used for suction itself is capable of generating larger thrust making it much more efficient and feasible to employ the MAV in future.