how calculating static margin for fling wing configuration

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the static margin of longitudinal stability can be calculated from

static margin = (AC-CP) / c

AC is the position of the aerodynamic center, CP is the Center of pressure, and c typically is the mean aerodynamic chord.

All three are not so easy to calculate. You may want to use a free tool such as

Aeolus Aero Sketch Pad

which does the work for you.

Best regards,


Use a XFLR

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