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