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

Helpful Tutorial: https://www.youtube.com/watch?v=N_oEZmDqm_Q

Airfoil Data: http://airfoiltools.com/search/index?m%5Bgrp%5D=naca4d&m%5Bsort%5D=1

Terms:

CD - drag coefficient

CL - lift coefficient

Airfoils and results:
Justin Fangzhi Wang (Deactivated) - NACA 4412

Brielle Chenier - NACA 2415

Cindy Cai (Deactivated) - NACA 1410

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

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