ESDU 87031
Wing angle of attack for zero lift at subcritical Mach numbers.

Abstract:
ESDU 87031 involves estimating separately two contributions to the zero-lift angle. One is due to camber, taken as that corresponding to the wing-root section and assumed constant across the span. The other is due to the combined effects of geometric twist and of camber dependent twist associated with spanwise camber changes from that at the root. The method applies to a wide range of cambered and twisted straight-tapered wings, provided the local effective twist is less than about 10 degrees and the flow is fully attached and subsonic at zero-lift. It can be applied to wings with cranked or curved edges using an "equivalent wing planform" as defined in ESDU 76003. The method correlates wind-tunnel test data drawn from a wide range of sources in the literature to within 0.3 degrees. Illustrations of typical uses for the method are given in the form of three worked examples.

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Data Item 87031
ISBN: 978 0 85679 624 1
DOI: 10.1912/ESDU87031a
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