SRCC - One Panel Canard Center of Grvity Calculator

One Panel Canard Center of Grvity Calculator



\|One Panel Standard Wing CG \| Two Panel Standard Wing CG \| One Panel Canard CG \| Two Panel Canard CG \|

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 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 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 more unstable and
    susceptible to stall at low speed, as during the landing approach.
    Also, for a better longitudinal stability, the canard should have a
    higher lift coefficient and stall at a lower geometric AoA than the
    main wing.

    For wings with two different panels click here