Figure 57: Glider Center of Gravity

The weight of the non-lifting parts is the sum of the fuselage, tailplane, and maximum load in the fuselage and must not exceed 400 kgs (882 lbs). Otherwise, the maximum load permitted in the fuselage must be correspondingly decreased. Datum Line: Front edge of the wing at the root rib. 150 XS G1 G2 GL = G1 + G2 600.24 a BE kg 360 365 370 375 380 385 390 395 400 Empty Weight Range of CG behind Datum Forward Aft lbs 794 805 816 827 838 849 860 871 882 mm 758 748 739 729 720 711 703 694 686 inches 29.84 29.45 29.09 28.70 28.35 27.99 27.68 27.32 27.01 mm 773 769 765 761 757 753 749 745 742 inches 30.43 30.28 30.12 29.96 29.80 29.65 29.49 29.33 29.21 b CG