Compression at the leading corner creates oblique shocks and a pressure rise. Along the line above the airfoil, the leading shock is crossed downstream of xA, and the expansion fan from the upper corner begins influencing that line downstream of xB, producing a continuous pressure decrease. The line below crosses its compression shock downstream of xA and stays at its elevated pressure over the drawn range. D shows the downstream shock crossings and the finite expansion-fan region; treating the pressure jump as located exactly at the surface corner or making the fan a discontinuous jump is incorrect.
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