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<-- __Chronological__ --> <-- __Thread__ -->

NACA 4-digit Airfoils

What Equation are Used to Genarate a NACA 4 and 5 digit Airfoil to Have a
Closed TRAILING EDGE. I have read Theory of Wing Section but the equatios
are for Open Trailing Edges.

Can any body point me where I can learn how to do this... Its Giving me a
Headache thanks....

<-- __Chronological__ --> <-- __Thread__ -->


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