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The vortex panel method improves on thin airfoil theory chiefly by

  • A.Accounting for compressibility at supersonic speed
  • B.Predicting the exact angle at which the section stalls
  • C.Representing the actual airfoil surface rather than the camber line
  • D.Including the effects of viscosity in the boundary layer

Answer: C

Panelling the true surface removes the thin-airfoil restriction and handles thickness properly, giving accurate pressure distributions for real sections. It remains inviscid, so it still predicts no drag and cannot find the stall.

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