Airfoil Shape

Using Mach Up: http://aero.go.usu.edu/mu5/ , wingspan should be between 7-9ft

Terms:

CD - drag coefficient

CL - lift coefficient

Airfoils and results:
@Justin Fangzhi Wang (Deactivated) - NACA 2415

@Cindy Cai (Deactivated) - NACA 1410

@Justin Fangzhi Wang (Deactivated) NACA 4412

Airfoil shape	Conditions & Geometry	Results

Airfoil shape	Conditions & Geometry	Results
NACA 1410	velocity: 10ft/s density: 0.093 slugs/ft^3 (styrofoam) angle of attack: 0 (in air gliding) geometry: 5° mount angle, 3° washout, 10° sweep, 2° dihedral root chord 1.5, tip chord 0.5
NACA 1410	^same as above except angle of attack: 15 degrees (lift-off??)
NACA 2415	velocity: 10ft/s density: 0.093 slugs/ft^3 angle of attack: 0 geometry: y-offset: 0.5 semi span: 4.0 3° mount angle, 0° washout, 2° sweep, 0° dihedral root chord 2, tip chord 1
NACA 0006	velocity: 10ft/s density: 0.0024 slugs/ft^3 angle of attack: -2 geometry: y-offset: 0.4 semi span: 4.0 0° mount angle, 3° washout, 5° sweep, -2° dihedral root chord 1.5, tip chord 1
NACA 4415	velocity: 10ft/s density: 0.0024 slugs/ft^3 angle of attack: 0 geometry: y-offset: 0.4 semi span: 4.0 0° mount angle, 0° washout, 5° sweep, 5° dihedral root chord 1.5, tip chord 1

Mechanical