Analysis Of Aircraft Drag

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Abstract - In this paper aircraft drag is considerably reduced by a design and change in deflection of wing even with the increase in speed of aircraft. Aircraft drag depends on the aspect ratio of the wing, thus by reducing the surface area and twisting the wing about its vertical axis (pivoted axis) to a particular angle without compromising the lift force generated, the drag force was considerably reduced. As a result a speed of 0.3 mach was raised to 1.2 mach experimentally non-symmetrical wing of various length nearer to 1m is designed, analyzed and deflected from its pivoted section, drag produced around the wing is drastically reduced. Drag produced at different angle is compared with the drag produced at 00 deflections and by reducing …show more content…

At low Mach numbers induced drag dominates drag concerns. Airplanes during takeoff and gliders are most concerned with induced drag. One way to reduce induced drag is to increase the aspect ratio of the lifting surface. At lower speeds, during takeoffs and landings, an oblique wing would be positioned perpendicular to the fuselage like a conventional wing to provide maximum lift and control qualities. As the aircraft gained speed, the wing would be pivoted to increase the oblique angle, thereby reducing the drag and decreasing fuel consumption.
At high speeds, both subsonic and supersonic, an oblique wing would be pivoted at up to 60 degrees to the aircraft's fuselage for better high-speed performance. Fig-1 Multiple exposure of aircraft showing wing positions
Oblique wing aircraft aircraft show large cross coupling in control and dynamic behaviour.

II.DRAG OVER THE WING
A.SELECTION OF AEROFOIL

An aerofoil is the shape of a wing. With low coefficient of drag an aerofoil is selected from various aerofoil of same Reynolds number and mach number.

Table – Selig aerofoil S4320

Name of airfoil
Alpha
Co-efficient of lift
Co-efficient of drag

S4320 0
5
10
15 0.094

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