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8.5.1: Optimization of Airfoil Zero-Coefficients

If one tries to generate an airfoil mean camber line with rough resolution and linear panel distribution from airfoil coordinates, the following problem will occur.
The zero-coefficients alpha-0 and Cm0 do not correspond with the values of the selected airfoil. Depending on panel resolution discrepancies of over 50% might occur.
In case of airfoils with reflexed mean line might if happen that the sign of the moment coefficient changes. This will have effects on all moments of the airplane and therefore even on the neutral-point and the centre of gravity.
A function was implemented to solve this problem. The new mean camber line is changed so that the zero-coefficients correspond to the original airfoil.

The alpha-0-, Cm0-Optimization is active, if the check mark is visible in the check box.



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