Study of a high-lift wing for a STOL light aircraft

Abstract

In this e-project is performed a study to find a proper wing design for a STOL capable electric light aircraft. This is the continuation of the e-project 1 realized in 2017 and the main objective is to find a final wing configuration capable of performing in the conditions required for the airplane, it is to say, STOL in tight spaces, electric plane with a decent range in order to be competitive and t has to fit all the internal components. The wing has to be ready to be implement it in the final design of the prototype of the plane. The main focus of the study is to find a suitable airfoil for the airplane, which fulfils all the requirements imposed by the project, then implement this airfoil into a wing, and then perform CFD simulations to obtain data about the boundary layer performance of the wing and be able to see, if the wing would be suitable for the airplane or if it is needed more research in other to find a suitable wing, capable of performing as desired.