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):
Wing Tip Chord (B):
Wing Sweep Distance (S):
Wing Half Span (Y):

Stabilizer Root Chord (AA):
Stabilizer Tip Chord (BB):
Stabilizer Sweep Distance (SS):
Stabilizer Half Span (YY):
Distance between both LE's (D):
*Stabilizer Efficiency^:**

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 =
Stabilizer 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 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 low Static Margin makes the aircraft tail-heavy and
    susceptible to stall at low speed, e. g. during the landing approach.
    ^* Choose Low Stabilizer Efficiency if the stab is close to the wing's wake
    or behind a fat fuselage in disturbed flow. Choose T-tail for most gliders.

      For wings with two different panels click here
      For wings with three different panels click here
      For wings with four different panels click here
      For wings with five different panels click here

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