Table 2. C_l, C_d and L/D for clean airfoil and sinusoidal TLE airfoil with 0.025c and 0.25c.

Airfoil	AoA	Cl	% decrease in lift	Cd	% increase in drag	L/D	% decrease in L/D ratio
Clean Airfoil	0	0.353		0.0177		20.00
Sinusoidal A 0.025c and W 0.25c	0	0.323	8.58	0.0190	7.53	17.7	15.0
Clean Airfoil	6	0.870		0.0341		25.51
Sinusoidal A 0.025c and W 0.25c	6	0.828	4.81	0.0329	-3.27	25.1	1.59
Clean Airfoil	12	1.19		0.818		14.6
Sinusoidal A 0.025c and W 0.25c	12	0.740	38.0	0.124	52.1	5.95	59.2
Clean Airfoil	18	0.799		0.232		3.44
Sinusoidal A 0.025c and W 0.25c	18	0.813	-1.65	0.247	6.46	3.28	4.52 (no improvement due to TLE)