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 (B1): 
Panel Chord2 (B2): 
Panel Chord3 (B3): 
Wing Tip Chord (B4): 
Wing Sweep Distance1 (S1): 
Wing Sweep Distance2 (S2): 
Wing Sweep Distance3 (S3): 
Wing Sweep Distance4 (S4): 
Wing Panel Span1 (Y1): 
Wing Panel Span2 (Y2): 
Wing Panel Span3 (Y3): 
Wing Panel Span4 (Y4): 
Stabilizer Root Chord (AA): 
Stabilizer Panel Chord (BB): 
Stabilizer Tip Chord (BB1): 
Stabilizer Sweep Distance (SS): 
Stabilizer Sweep Distance (SS1): 
Stabilizer Panel Span1 (YY): 
Stabilizer Panel Span2 (YY1): 
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 Stabiliser Efficiency if the tail is close to the wing's wake
    or behind a fat fuselage in disturbed flow. Choose T-tail for most gliders.

    For wings with single panel click here
    For wings with two different panels click here
    For wings with three different panels click here
    For wings with five different panels click here


Calculate Wing Loading
Wing Area :  sq. in
sq. dm
Aircraft Weight :  ounces
Max Lift Coefficient :  Max Cl.
WING LOADING :  oz/sq.ft
CUBIC LOADING :  oz/cubic.ft

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