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Mar 04, 2004, 05:16 PM
Registered User

Slight correction

1/.866 thicker (e.g., a 10% foil will behave like a 15.5%
I guess I got a little sloppy too. Correcting my example, 1/.8667 ~= 1.155, or 11.55%, not 15.5%. I dropped a 1 when typing my response. Not quite as big an impact, but a positive impact just the same.
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Mar 04, 2004, 05:22 PM
Registered User
Reading my response I guess I ought to add back in what I left out to TRY to avoid crreating any more confusiion. At 30% sweep for the example, the 10% foil will appear aerodynamically like an 11.55% foil relative to the quarter cord normal flow component.
Jan 25, 2013, 02:15 AM
Registered User

Airfoil section for swept wings

if the airfoil section is oriented perpendicular to the quarter chord line then what did they do near leading and trailing edge.. kindly reply to sort out the problem of mine...
Jan 25, 2013, 11:34 AM
Ascended Master
Sparky Paul's Avatar
That is a very vague question... The differences in thickness with sweep have been explained. What problem do you perceive at the leading and trailing edges?
These are both continuous along the span, nothing unusual at all going on.

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