Atec 321 FAETA - Page 44

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 44 of 56
8.5. Centre of gravity determination
The aircraft must be balanced in “flight position” including crew and fuel.
Weight on main wheels G
1
(kg)
Weight on nose wheel G
2
(kg)
Total weight G
1
+ G
2
G = G
1
+ G
2
(kg)
Distance from main wheel axis to nose wheel axis x
MW-FW
= 1,44 (m)
Distance from main wheel axis to wing leading
edge in wing root area x
MW-LE
= 0,76 (m)
CG distance from main wheel axis x
MW-CG
= G
2
* x
MW-FW
/ G (m)
Length of MAC b
MAC
= 1,112 (m)
Length of wing chord in the root area b = 1,300 (m)
Back-swept MAC displacement s
y
= 0,19 (m)
Distance from CG to leading edge x
CG
= x
MW-LE
– x
MW-CG
(m)
Distance from CG to leading edge of MAC x
CG-MAC
= x
MW-LE
– x
MW-CG
– s
y
=
= 0,57 – 1,44 * G
2
/ G (m)
x
CG-MAC%
= x
CG-MAC
* 100 / 1,112 =
= 51,26 – 129,5 * G
2
/ G (%)