Canard Center of Gravity Calculator
Aerodynamic Center (AC), Mean Aerodynamic Chord (MAC), Center of Gravity (CG), Neutral Point (NP) and Wing Area
Canard Root Chord (A): 
Canard Tip Chord (B): 
Canard Sweep Distance (S): 
Canard Half Span (Y): 
Wing Root Chord (AA): 
Wing Tip Chord (BB): 
Wing Sweep Distance (SS): 
Wing Half Span (YY): 
Distance between both LE's (D): 
Enter Static Margin, then
Mean Aerodynamic Chord MAC = 
Sweep Distance at MAC (C) = 
From Root Chord to MAC (d) = 
From Canard Root LE to AC = 
From Canard Root LE to NP = 
From Canard Root LE to CG = 
Wing Area = 
Canard Area = 
Wing Aspect Ratio = 
Foreplane 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 tail-heavy aircraft will also be unstable and susceptible
    to stall at low speed, as during the landing approach.
    Further, for a better longitudinal stability, the canard should have
    higher lift coefficient and stall at lower geometric AoA than the
    main wing.

    For wings with two 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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