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9.5. Centre of gravity determination
The aircraft has to be weighed at flight position including pilot and fuel.
Weight on main wheels G
1
(kg)
Weight on tail wheel G
2
(kg)
Total weight G = G
1
+ G
2
(kg)
Wheel base x
MW-TW
= 3,7 (m)
Distance from main wheel centre to leading edge
of wing in root point x
MW-LE
= 0,19 (m)
CG distance from main wheel centre x
MW-CG
= G
2
* 3,7 / G (m)
Length of MAC b
MAC
= 1,032 (m)
Length of wing chord in the root area b = 1,19 (m)
Back-swept MAC displacement s
y
= 0,088 (m)
CG distance from leading edge of wing
in root point x
LE-CG
= x
MW-LE
+ x
MW-CG
=
= 0,19 + 3,7 * G
2
/ G (m)
Distance from CG to leading edge of MAC x
CG-MAC
= x
LE-CG
– s
y
=
= 0,102 + 3,7 * G
2
/ G (m)
x
CG-MAC%
= x
CG-MAC
* 100 / 1,032 =
=9,884 + 358,5 * G
2
/ G (%)
9.6. Useful weight, weight table
Useful weight is a difference between maximum take-off weight and the weight of empty
aircraft.
The useful weight by empty weight ………………………. kg is ………………………. kg.
The weight table
Fuel tank 50 l
1 l = 0,775 kg
Pilot weight kg
incl. 5 kg luggage
CG % MAC Total weight
of aircraft kg
¼ ………. 12,5 l
½ ………. 25,0 l
¾ ………. 37,5 l
1 ……….. 50,0 l