Aircraft Center of Gravity Calculator

Aircraft Center of Gravity Calculator
Aerodynamic Center (AC), Mean Aerodynamic Chord (MAC), Center of Gravity (CG), Neutral Point (NP) and Wing Area


Wing Root Chord (A):
Panel Chord1 (B):
Wing Tip Chord (B2):
Wing Sweep Distance1 (S):
Wing Sweep Distance2 (S2):
Wing Panel Span1 (Y):
Wing Panel Span2 (Y2):

Stabiliser Root Chord (AA):
Stabiliser Tip Chord (BB):
Stabiliser Sweep Distance (SS):
Stabiliser Half Span (YY):
Distance between both LE's (D):
Type of Stabiliser:

Enter Static Margin, then	%

Mean Aerodynamic Chord MAC =
Sweep Distance at MAC (C) =
From Root Chord to MAC (d) =
From Wing Root LE to AC =
From Wing Root LE to NP =
From Wing Root LE to CG =
Wing Area =
Stabiliser Area =
Wing Aspect Ratio =
Tail Volume Ratio, Vbar =

    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 gives a more 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.
    A tail-heavy aircraft will also be more unstable and susceptible
    to stall at low speed, e. g. during the landing approach.

    For wings with a single panel click here

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