Once the critical angle of attack is reached (generally around 14 degrees) the aerofoil will stall. The subsequent loss of static pressure creates a pressure difference between the upper and lower surfaces that is called lift and opposes the weight of an aircraft (or thrust that opposes drag).Īs the angle of attack (the angle between the chord line and relative air flow) is increased, more lift is created. Basically this states that total pressure is equal to static pressure (due to the weight of air above) plus dynamic pressure (due to the motion of air).Īir that travels over the top surface of the aerofoil has to travel faster and thus gains dynamic pressure. You may need opposite aileron to maintain your bank angle, and prevent over-banking. This creates asymmetric lift, causing the aircraft to exhibit an over-banking tendency. The basic principle behind an aerofoil is described by bernoullis theorem. When youre established in a steep turn, your outer wing moves slightly faster through the air then the inner wing. Alternatively, a jet would have a thin wing with minimal camber to allow it to cruise at high speeds. For example, a crop duster may have a thick, high camber wing that produces a large amount of lift at low speed. Point of Maximum Thickness = Thickest part of the wing expressed as a percentage of the chordīy altering each of the above features of an aerofoil, the designer is able to adjust the performance of the wing so that it is suitable for it's particular task.Denotes the amount of curvature of the wing Mean Camber Line = Line drawn half way between the upper and lower surface of the aerofoil.Chord = Line connecting the leading and trailing edge.Trailing Edge = Aft edge of the aerofoil.Leading Edge = Forward edge of the aerofoil. ![]() ![]() Several terms are used to describe aerofoils (Dynamic Flight, 2002).
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