Engineering
Airfoil Pressure Coefficient
C_p ≈ −4·(x/c)·(1 − x/c)
The suction side of an airfoil sees strongly negative pressure coefficients, peaking near mid-chord where the flow accelerates fastest over the curved surface.
Computed & rendered in pure C# on the frozen OnlyCSharp 1.8 library — animation baked to GIF with the library's own
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