Spanwise lift distribution on a wing
I was wondering if anyone knew how to create a lift distribution curve along the span of a wing? I would prefer it in a numerical form so I can export it to excel to compare to other experimental data. The only way I can think to do it is to create tons of sections and integrate the pressure of the section intersections with the wing but this is a lot of work and not as accurate as should be possible.
Also does anybody know how to subtract out the hydrostatic pressure of a "flatwave" from the pressure in ccm+? I ask because I have tried writing a field function that that was the the $pressure-$hydrostaticpressureofflatwave0 and it would not compile.
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