<Dd> A specific chord line of a tapered wing . At the mean aerodynamic chord, the center of pressure has the same aerodynamic force, position, and area as it does on the rest of the wing . The MAC represents the width of an equivalent rectangular wing in given conditions . On some aircraft, the center of gravity is expressed as a percentage of the length of the MAC . In order to make such a calculation, the position of the leading edge of the MAC must be known ahead of time . This position is defined as a distance from the reference datum and is found in the aircraft's flight manual and also on the aircraft's type certificate data sheet . If a general MAC is not given but a LeMAC (leading edge mean aerodynamic chord) and a TeMAC (trailing edge mean aerodynamic chord) are given (both of which would be referenced as an arm measured out from the datum line) then your MAC can be found by finding the difference between your LeMAC and your TeMAC . </Dd> <P> Center of gravity (CG) is calculated as follows: </P> <Ul> <Li> Determine the weights and arms of all mass within the aircraft . </Li> <Li> Multiply weights by arms for all mass to calculate moments . </Li> <Li> Add the moments of all mass together . </Li> <Li> Divide the total moment by the total mass of the aircraft to give an overall arm . </Li> </Ul> <Li> Determine the weights and arms of all mass within the aircraft . </Li>

How to calculate centre of gravity in an aircraft
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