Aerodynamic Study of Span Wise Morphing Wing

The frame of the wing, type of the wing and camber angles derive its own aerodynamic characteristic properties. However, innovations and development in new technology are pushing the concept of a wing that can vary its camber and shape to widen its operating conditions to give maximum aerodynamic efficiency. This would make it able to adapt itself to different flight conditions. Present research deals with improvement in the operation and aerodynamic performance at various altitude conditions (like takeoff, cruise, landing, etc). These improvements accomplished during viscous drag compromising by encouraging laminar flow over the wing. To reach such aerodynamic abilities, at any rate of flow conditions, the exterior part of the wing is subjected to twist (in-flight morphing) to maintain the drag as/at? lowest achievable value. This paper discusses designing a span wise morphing wing, which allows a change in the aspect ratio while, at the same time, supporting structural wing loads. The aerofoil of the wing is designed using NACA 0012, increase in wing aspect ratio and span ratio is calculated. Using FLUENT, an ANSYS CFD solver, the performance and its aerodynamic nature of each wing shape of the span, morphing about 20% and 40%, are concluded.