Consider a CFD simulation of a nominal wing configuration having a span of 1 meter
and operating at an angle of attack of 5 degrees. Images depicting the resulting
pressure field on the wing as well as the surface mesh are shown in Illustration 1 and 2.
For design purposes, the client is interested in knowing what the integral loading on the
wing is at 10 discrete air stations along the span. To provide this data to the client, it is
necessary to integrate the forces on the wing over the 10 different regions of interest.
Each air station has a constant width of .1 m. The air stations are depicted graphically
in Illustration 3.
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