![]() ![]() For this purpose, NACA 2412 Airfoil which has a maximum camber of 2% located at 40% (0.4 Chords) from the leading edge with a maximum thickness of 12% of the chord & NACA 3412 which has a maximum camber of 3% located at 40% (0.4 Chords) from the leading edge with a maximum thickness of 12% of the chord are employed. Here we are going to analyse the impact of increase in the percentage of camber on the ratio of CL/CD. The amount of laminar flow can be maximised on a straight wing by using very carefully tailored shapes to move the maximum thickness very far aft on the wing. We focused our research on a straight wing. Here in this paper, we are trying to increase the CL/CD ratio by increasing the percentage of the camber in the NACA airfoil. FOM is the ratio of the section maximum lift coefficient (CL, max) to the cruise section profile drag coefficient (CD). In order to minimize the wing profile drag the figure of merit (FOM) applicable to aircraft should be maximized. The wing profile for most aircraft is of airfoil- shaped. ![]() Designers main focus is on the design optimisation of the wing profile so as to reduce the drag and thus obtaining better fuel efficiency and overall performance of the aircraft. Comparison of Aerodynamic Performance of Aircraft Wing by Changing the Maximum Camber As Percentage of the ChordĪbstract In transport aircraft, the wing contributes about 1/3rd of the total aircraft drag. ![]()
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