Application of the formula SPAN x SPAN : WING AREA will giveQuestion 3Select one:a.Wing loadingb.Fineness ratioc.Mean aerodynamic chordd.Aspect ratio

Application of the formula SPAN x SPAN : WING AREA will give

The ratio of the wing span to the wing chord is theQuestion 4Select one:a.Aspect ratiob.Fineness ratioc.T/C ratiod.Load ratio

A fully loaded boeing aircraft has a mass of 5.4×105 kg. Its total wing area is 500 m2. It is in level flight with a speed of 1080 km h−1. If the density of air ρ is 1.2 kg m–3, the fractional increase in the speed of the air on the upper surface of the wing relative to the lower surface in percentage will be

The main factors that produce lift from a wing areQuestion 17Select one:a.Camber, angle of attack and airspeedb.Dihedral, camber and airspeedc.Chord, angle of attack and airspeedd.Angle of attack, camber and chord

The figures shown in the options are schematics of airfoil shapes (not to scale).For a civilian transport aircraft designed for a cruise Mach number of 0.8, whichamong them is aerodynamically best suited as a wing section?(A)(B)(C)(D)