Thin airfoil theory

Thin Airfoil Theory l

y  V

x

m • Lift coeffcient: Cl  l / 12 V2 c

• Moment coeficient: Cm  m / 12 V2 c 2 • Center of pressure: • Aerodynamic Center:

Point about which moment is zero Point about which moment does not change with angle of attack

1

Thin Airfoil Theory – Setup Symbols:

v=Vsin+v'

y

u=Vcos+u'

u  V

t c l (