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Enter the variables at left using the same units for all entries.
For an aircraft to be stable in pitch, its CG must be forward of the
Neutral Point NP by a safety factor called the Static Margin, which
is a percentage of the MAC (Mean Aerodynamic Chord).
Static Margin should be between 5% and 15% for a good stability.
Low Static Margin gives less static stability but greater elevator
authority, whereas a higher Static Margin results in greater static
stability but reduces elevator authority.
Too much Static Margin makes the aircraft nose-heavy, which
may result in elevator stall at take-off and/or landing.
Whereas a tail-heavy aircraft will also be unstable and susceptible
to stall at low speed, as during the landing approach.
For a better longitudinal stability, the canard should have higher lift
coefficient and stall at lower geometric AoA than the main wing.
A pusher prop is therefore advisable, since with a tractor prop, the
prop-wash may prevent the canard from stalling before the wing.
For wings with a single panel click
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