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behaviour of the NACA4412 aerofoil is shown in Figure A3.20 for angles of attack below and just above the stall. Positive lift occurs at zero angle of attack. Zero lift occurs at a small negative angle of attack of approximately −4°.

      (A3.8)upper C Subscript m Baseline equals StartFraction italic Pitching slash italic unitspan Over one half rho upper U squared c squared EndFraction

Schematic illustration of the classification of the NACAXXXX aerofoil range. Graphs depict the characteristics of the NACA4412 aerofoil for Re = 1.5·106.

      then there will be a position, called the aerodynamic centre, for which StartFraction italic d upper C Subscript m Baseline Over italic d upper C Subscript l Baseline EndFraction equals 0. Theoretically, the aerodynamic centre lies at the quarter‐chord position and is close to this point for most practical aerofoils.

      The value of Cm depends upon the degree of camber, but for the NACA4412 the value is −0.1. Note that pitching moments are always negative in practice (nose down) despite the sign convention.

      Above the stall the pre‐stall position of the aerodynamic centre usually continues to be used, although no longer satisfying the above definition.

      1 1 There is not complete agreement on the appropriate name for this limit because Lanchester (1915), Betz (1919, 1920), and Joukowski (1920) all published relevant papers. Betz limit is the most commonly used name. See also comment in Chapter 1.

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