chosen point: x = 1.1, y = 0.225
<aside> 🍓 WS = 1.1
TW = 0.225
</aside>
tighter:
[Results]
static margin: 5.4%, CG @ 25.3% chord.
MTOW estimate = 4.14 lbs.
Planform Area S = 505.1731
Fuselage Definitions: Total Length 43.91 in.
Nose Section: 8.0000 in.
Main Section: 14.5083 in.
Aft Section: 20.8000 in.
Wing Definitions: Location from nose: 9.40 (in.)
Wingspan: 55.05
Root chord: 13.11
Tip chord: 5.24
LE sweep: 4.09 deg.
Empennage Definitions: (in.)
hstab:
chord 4.6496
span 18.5982
vstab:
chord 4.9206
span 7.3809
Landing Gear Placement: (dist. from nose, in.)
NLG: 8.0000
MLG: 17.0780
more lax
[Results]
static margin: 7.7%, CG @ 27.3% chord.
MTOW estimate = 4.14 lbs.
Planform Area S = 505.1731
Fuselage Definitions: Total Length 44.21 in.
Nose Section: 8.0000 in.
Main Section: 14.2083 in.
Aft Section: 21.1000 in.
Wing Definitions: Location from nose: 9.10 (in.)
Wingspan: 55.05
Root chord: 13.11
Tip chord: 5.24
LE sweep: 4.09 deg.
Empennage Definitions: (in.)
hstab:
chord 4.6269
span 18.5078
vstab:
chord 4.8967
span 7.3451
Landing Gear Placement: (dist. from nose, in.)
NLG: 8.0000
MLG: 17.0399
if the planes we make tends to be tail heavy,
and neutral point is a purely geometric constraint