sin αst

LIST OF ATTACHMENTSAIRFOIL
With the following constants
144
Coefficient Cl Cd
k0 4.002e-1 7.027e-3
k1 1.112e-1 -5.823e-4
k2 -3.778e-3 1.344e-4
k3 4.785e-4 1.970e-6
k4 -2.714e-5 0.000e-0
Table D.1: Polynomial constants for 0� < � < 13�
For angles in the post-stall region the lift and drag coefficient values are predicted using a
method developed by Viterna and Corrigan [16, p. 65]. The method assumes zero twist
angle and maximum drag coefficient Cd,max at an inflow angle � = 90�. The latter is set to 1
in accordance with [46, p. 18].
The drag coefficient Cd is defined by [16, p. 65]
Where
Cd.st is the drag coefficient at stall.
The lift coefficient Cl is given by
Where
Cl.st is the lift coefficient at stall.
Cd B1sin ( �)
2 = � B2cos ( �)
1
B2 =
cos �st B1 = Cd.max � �
� � Cd.st Cd.max sin ��st� 2
�
Cl = A1 sin ( 2�)
� A2 B1 A1 =
2
A2 =
Cl.st � Cd.max sin �st cos( �)
2
sin ( �)
� � � cos� �st�� sin � � st�
� �2 cos � st
(D.2)
(D.3)
(D.4)
(D.5)
(D.6)
(D.7)