Discussion
At supersonic speed the lift curve slope of a thin aerofoil varies as
Answer: B
Ackeret theory gives \( 4/\sqrt{M^{2}-1} \) for a thin section in supersonic flow, so the slope falls as Mach number rises well above unity. The second expression is the subsonic Prandtl-Glauert form, which diverges at \( M = 1 \) and is invalid above it. A Mach-independent \( 2\pi \) is the incompressible result. Sweep matters supersonically too, but it modifies the result rather than replacing the Mach dependence.
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