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Wing Root Chord (A): |
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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 most be forward of the
Neutral Point NP by a safety factor
caled 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 gives a more static
stability but
lesser elevator authority.
Too much Static
Margin makes the aircraft nose-heavy, which
may result in elevator stall at take-off
and/or landing.
A tail-heavy aircraft will also
be more unstable and susceptible
to stall at
low speed, e. g. during the landing approach.
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Wing Tip Chord (B): |
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Wing Sweep Distance (S): |
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Wing Half Span (Y): |
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Stabiliser Root Chord (AA): |
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Stabiliser Tip Chord (BB): |
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Stabiliser Sweep Distance (SS): |
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Stabiliser Half Span (YY): |
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Distance between both LE's (D): |
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Enter Static Margin, then |
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Mean Aerodynamic Chord MAC = |
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Sweep Distance at MAC (C) = |
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From Root Chord to MAC (d) = |
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Static Margin % of MAC = |
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From Wing Root LE to AC = |
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From Wing Root LE to NP = |
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From Wing Root LE to CG
= |
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Wing Area
= |
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Stabiliser Area
= |
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