AERODYNAMIC ANALYSIS OF SEAMLESS HORIZONTAL STABILIZER

This project presents an investigative view into the concept of seamless aeroelastic wing and hingeless flexible trailing edge. Wings are designed in a fashion to provide maximum lift and minimal drag and weight. But with conventional wings where rivets are used and the control surfaces are separately hinged, parasite drag comes into play. This project is about analysing a smooth seamless wing with hinge-less flexible trailing edge. This type of wing reduces the drag considerably and the hinge-less trailing edge leads to a minimal control demand and reduces the noise produced when the aircraft comes for landing. Seamless aeroelastic wing will function as an integrated one piece lifting generating surface. It is designed to produce a desirable wing camber for control by deflecting a hinge-less flexible trailing edge part instead of a traditional hinged surface. This kind of flexible wing can be achieved either by a curved beam and disc actuation mechanism or by piezo-electric materials, whose shape change can be achieved by electricity. This method of shape changing is termed morphing and in recent times has been researched into with helicopter blades and aircraft wings. The aerodynamic merits of seamless wing over the conventional wing design can by projected by the use of computational fluid dynamics. The intent of this project is to analyze the effects of introducing the concept of Seamless Wing to the horizontal stabilizer. While the removal of rivets and serrations that hinge the elevators to the stabilizer reduces the overall drag by a reasonable value, the overall concept of a