Discussion
The lift curve slope of a thin two-dimensional aerofoil in incompressible flow is
Answer: B
Thin aerofoil theory gives \( 2\pi \) per radian, about 0.11 per degree, and it is the anchor value every finite-wing estimate is reduced from. Half that would be a very low slope no practical section shows. Four times \( \pi \) is the value sometimes quoted for a flat plate in supersonic flow at low Mach number in error, and \( 4/\sqrt{M^{2}-1} \) is the correct supersonic form. Unity per radian is far too small and would describe a very low aspect ratio surface.
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