Paper Title
In-Flight Camber Transformation Of Aircraft Wing Based On Variation In Thickness-To-Chord Ratio

In general, there is wide gap between subsonic flight and supersonic flight, mainly due to aerodynamic limitations. This paper presents a method for development of next generation aircraft wings whose camber can be transformed in-flight for enabling it to fly efficiently in different regimes of Mach number; say, Subsonic to supersonic and vice-versa. To demonstrate the aerodynamic performance of the subsonic airfoil (C141A) and a supersonic airfoil (NACA 65206), the flow is simulated by using the commercial program GAMBIT and FLUENT. An important aspect is the mechanical and hydraulic transformation mechanism working inside the wing which helps it to change the camber according to the requirement. For this mechanism, a Hydraulic expansion-contraction system is used which works on the principle of Master and Slave Piston-cylinder arrangement. This concept can be practically very important to increase aerodynamic efficiency of the aircraft in different regions of subsonic, transonic and supersonic flights. Moreover, this idea of real-time camber transformation can make an aircraft multipurpose in accordance to Mach regime of flight.