Abstract
A NACA 6-series is one of the most commonly used commercial passenger aircraft, which is of subsonic and transonic type. This series, a laminar flow type is taken for our study. In this paper the straight wing and the swept back wings are designed using a suitable tool and it is simulated by using CFD software. FLUENT software is used to analyse the different swept angles of 0°, 25°, 30°, 35°, 40° and 45° for different mach numbers ranging from 0.6 to 1.2. Based on these results the drag coefficient (CD ) and lift coefficient (CL ) are plotted. The values for the straight and swept wings indicate that there is a reduction in drag coefficient. Then thus by means of optimisation factor the swept angle is optimised for the NACA 6-series air foil. By the help of the optimising factor we have found that 35° will be more efficient and it is the best choice for a high speed aircraft, because this wing minimises fuel consumption and thereby by remarkably reducing wave drag during flight thus reducing the cost of flight and increase the range of aircraft and at the same time it ensures a safe take-off and a smooth landing.
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