Quote:
Originally Posted by ennored
A little reality check on the math though....
35 times the frontal area? That means it has 1/35 the drag coefficient, right?
1/35 = .029
IF the coefficient for the round shape was 1 (it must be less, but follow along), the coefficient for the airfoil is .029? Seems too low, even for a section of a chord? Someone has some numbers, right?
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When the chord length of the airfoil section equals 167X the diameter of the wire,the drags are identical.
Bear in mind that we might be considering a length of crude circular wing support on an ultralight aircraft to a length of wing on a Lear Jet.
It's 2-dimensional flow,so not real helpful for automotive applications,however it does illustrate potentialities with respect to streamlining.