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By E. Houghton, P. Carpenter

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At angles of incidence around 18" or 20" the pressure reduction on the upper surface suddenly collapses and what little lift remains is due principally to the pressure increase on the lower surface. A picture drawn for one small negative incidence (for this aerofoil section, about -4") would show equal suction effects on the upper and lower surfaces, and the section would give no lift. At more negative incidences the lift would be negative. 5). 6. In either case, the pitching moment coefficient is measured about some definite point on the aerofoil chord, while for some particular purpose it may be desirable to know the pitching moment coefficient about some other point on the chord.

23 for a two-dimensional (infinite span) wing. Considering first the full curve (a) which is for a moderately thick (13%) section of Basic concepts and definitions 45 Fig. 23 Typical lift curves for sections of moderate thickness and various cambers zero camber, it is seen to consist of a straight line passing through the origin, curving over at the higher values of CL,reaching a maximum value of C,, at an incidence of as,known as the stalling point. After the stalling point, the lift coefficient decreases, tending to level off at some lower value for higher incidences.

5. The corresponding value of aswould be around 18". Curves (b) and (c) in Fig. 23 are for sections that have the same thickness distribution but that are cambered, (c) being more cambered than (b). e. to shift the whole lift curve somewhat to the left, with negligible change in the value of the lift-curve slope, or in the shape of the curve. This shift of the curve is measured by the incidence at which the lift coefficient is zero. This is the no-lift incidence, denoted by 00,and a typical value is -3".

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