Abstract
Wings are the main lift generating sources for any aerospace vehicle. The performance of an airborne vehicle largely depends on its wing design. Wing design is a complex process involving selection of many parameters called the wing design parameters. These parameters differ for different wing configurations. As per the mission requirement, these parameters are selected optimally. The main focus in this study is to understand wing design methodologies. It is necessary to understand how much lift has to be generated, what the required wing loading is and what will be the flight conditions where this wing will be used. A standard 3D wing validation has been completed before the designed wing aero-analysis is performed. With this validation the wing design methodology has been verified and standardized to be applicable for similar type of wing design in future. at initial stage the standard wing validation case has been studied. wing geometry has been modeled and full viscous flow has been calculated for the range of Mach no 0.7 and 0.84 at angles of attack 0 to 6.5 at the same Reynolds number (at which Wind Tunnel test has been carried out), to validate the CFD methodologies.
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