36
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
= 0,158
(m)
CG distance from leading edge of wing
in root point
x
LE-CG
= x
MW-LE
+ x
MW-CG
=
= 0,19 + G
2
* 3,7 / G
(m)
Distance from CG to leading edge of MAC
x
CG-MAC
= x
LE-CG
– s
y
=
= 0,032 + 3,7 * G
2
/ G
(m)
x
CG-MAC%
= x
CG-MAC
* 100 / 1,032 =
= 3,1 + 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
Summary of Contents for 212 SOLO
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