Improvement of Aerodynamic Performance in Floatplane Wings with Installation of Winglets

Wing tip structures have become a standard design solution in modern airliners due to their ability to improve aerodynamic efficiency, reduce fuel consumption and consequently improve the environmental impact introduced by air transport. Their ability to interact with and modify vortex sheets also influences flight dynamics. This work focuses on the use of winglets in floatplanes to both improve aerodynamic efficiency and modify flight dynamics. Floatplanes are versatile aircraft suited to operate in remote regions where other means of transportation are not available. However, the floats, which confer the ability to take-off and land in water, introduce undesirable aerodynamic effects in flight, which are normally adjusted with the use of a set of tail-installed surfaces. CFD simulations using ANSYS CFX were carried out at flight conditions to assess the performance of winglets on a tapered NACA23012 wing. A model of the wing was tested in a wind tunnel for relevant angles of attack and speeds of 5-35 m/s. A second wing design (rectangular NACA23017 root and tapered NACA23012 tip) was additively manufactured in Nylon PA-12 for further tests. The wing lift and drag have been evaluated. The effects of the previously mentioned modification in the control forces and stability on this aircraft will be considered, and compared with the effectiveness of other more commonly used control measures, and how the aerodynamic efficiency of the proposed aircraft has changed. The main results will be presented and discussed.