>>Barring that, in figuring out the area of a single wing panel, >>tapered leading edge and straight trailing edge, is the following >>formula correct? .5 * (panel span * (root chord + tip chord))
What you've suggested is correct. For anything other than the ideal of straight TE and single taper LE, though, this would be an approximation.
BTW; With some graph paper, a protractor, tape measure and a straight edge you can do a fair job of approximating. But if you want to do it right, as I've said before, use a CAD program. Makes lift so much easier and creates pretty pictures too.
Bill Swingle Janesville, CA [EMAIL PROTECTED]
RCSE-List facilities provided by Model Airplane News. Send "subscribe" and "unsubscribe" requests to [EMAIL PROTECTED] Please note that subscribe and unsubscribe messages must be sent in text only format with MIME turned off.
