Weight and balance calculator
Centre of gravity is a weighted average of moment arms. Being outside the envelope changes the handling in ways the aircraft was never tested for.
Centre of gravity
2.2094m
- Total weight
- 1096.4
- Within weight and balance limits
- 1
- Margin under maximum weight
- 53.6
- Position in the CG envelope
- 34.9 % Inside the envelope
- Total moment
- 2422.4 kg m
- Fuel weight
- 86.4
- Payload available
- 313.6
Show the working
- Empty weight = 750
- Empty weight arm = 2.1
- Front seats = 160
- Front seat arm = 2.05
- Rear seats = 80
- Rear seat arm = 3
- Fuel = 120
- Fuel arm = 2.4
- Baggage = 20
- Baggage arm = 3.6
- Maximum take-off weight = 1150
- Forward CG limit = 2
- Aft CG limit = 2.6
- Fuel weight = 120 * 0.72 = 86.4
- Total weight = 750 + 160 + 80 + 86.4 + 20 = 1096.4
- Total moment = 750*2.1 + 160*2.05 + 80*3 + 86.4*2.4 + 20*3.6 = 2422.36
- Centre of gravity = 1096.4 > 0 ? 2422.36 / 1096.4 : 0 = 2.209 38
- Margin under maximum weight = 1150 - 1096.4 = 53.6
- within_weight = 1096.4 <= 1150 ? 1 : 0 = 1
- within_cg = 2.209 38 >= 2 && 2.209 38 <= 2.6 ? 1 : 0 = 1
- Position in the CG envelope = (2.6 - 2) > 0 ? (2.209 38 - 2)/(2.6 - 2)*100 : 0 = 34.896
- Within weight and balance limits = 1 > 0 && 1 > 0 ? 1 : 0 = 1
- Payload available = 1150 - 750 - 86.4 = 313.6
Values are shown to six significant figures here; the arithmetic itself runs on exact fractions and is only rounded where a number is printed.
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The formula
- moment = weight x arm
- centre of gravity = total moment / total weight
- avgas at 0.72 kg per litre
An aft CG makes an aircraft less stable and can make a spin unrecoverable. A forward CG raises stall speed and take-off distance.
This is a planning and study tool. Use certified charts, an approved flight manual and official publications for anything operational.