• aerodynamic
• aerodynamics
• aircraft
• amphibious
• CFD
• design
• fluid dynamic
• fluid dynamics
• IDINTOS
• Plane
• Prandtl
• PrandtlPlane
• ultra-light

This master thesis is involved in the IDINTOS project, and in particular it studies the preliminary aerodynamic design concerning the stability in cruise conditions, and the flapped configuration of a PrandtlPlane aircraft.
Starting from a preliminary CAD design, both stability and equilibrium were investigated in cruise conditions. In fact, the first part of the study presents the CAD model of the original geometry and both set-up and results of the CFD simulations. By knowing Lift, Drag and Moment and their coefficients (Cl, Cd and Cm), it is possible to create new geometries in order to reach the optimum configuration, which implies that the point of resultant Lift is as closer as possible to the center of the mass CG and that the configuration itself is stable.
The second part is focused on both the take-off and the landing conditions. The flapped configuration is designed in order to develop enough Lift and appropriate aerodynamic Moment. The anterior wing was flapped with a fowler flap system that is the most performant one regarding the generated Lift. At first, the flap airfoil was chosen. The main phase of the flap design was to define the optimum position of the flap with respect to the trailing edge of the anterior wing. To achieve this goal detailed maps of Cl with respect to the flap position were made at different angles of attack and angles of flap deflection.
Regarding the posterior wing, a plain flap system was chosen and different angles of deflection of it were investigated in order to obtain the requested Lift and, above all, to equilibrate the aerodynamic Moment of the anterior flapped wing. In the end, the trends of both Cl and Cm with respect to the angle of attack were plotted to understand the range of the angles of attack in which the configuration was equilibrated and stable.