The bursting of leading edge laminar separation bubbles that can occur on moderately thick airfoil sections is the cause of sudden large increase in drag, decrease of lift, and change in pitching moment associated with abrupt stall. This paper decribes a calculation of the bursting of laminar separation bubbles. To analyze separated flows without meeting any singularity at the separation point, Navier-Stokes equation is solved under the condition of precribed external velocity distribution.
