Speedy Aerodynamics vroosh vroosh

Datum: LE of wing @ root

<aside> 💡 Results 8.22.24 keep all surface geometries from original glider, shift them to new locations LE of hstab starts 0.9m away from LE of main wing

</aside>

Empennage Constraints

left a spacing of 10mm between TE of hstab and LE of vstab
made the hstab 25mm above the vstab datum
vstab datum is 80mm below the main wing datum

Empennage Definitions

Airfoil used: NACA 0012

no angle of incidence needed for the htail.

	Vstab	Hstab
Taper Ratio	0.4703	0.5259
Aspect Ratio	1.8137	5.2922
original area	0.0564604	0.0759532
(original volume coeff)

vstab reference.

hstab reference.

Wing Definitions

wing reference.

Main Wing datum (x, y, z) = (0, 0, 0)
Airfoil: HQ3.0-11

	inboard section: span = 1.150, LE sweep = 0, dihedral = 0
	root chord: 0.229
		(Xle, Yle, Zle) = (0, 0, 0)
		Ainc: 2
	tip chord: 0.1834
		(Xle, Yle, Zle) = (0, 1.150, 0) 
		Ainc: 2
	outboard section: span (geometric) = 0.730, LE sweep = 0, dihedral = 2 deg.
	tip chord: 0.1058
		(Xle, Yle, Zle) = (0, 0.73*cos(2deg), 0.73*sin(2deg))
		Ainc: 1.25

CG lower bound	30% root chord	0.0687m
CG upper bound	35% root chord	0.08015m

target CG to be at exactly 35% chord, location of main wing max thickness = 8cm ****from datum.

(tolerance -1 + 0 cm)

Static Margin (purely geometric)

MAC: 0.19038m