V-Tail Root Section Maximum Lift Coefficient

See Graphic

NACA Airfoil

Sectional Maximum Lift Coefficient,

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0006

0.92

0009

1.32

0012

1.50

1408

1.35

1412

1.58

2412

1.68

2418

1.47

2424

1.29

4412

1.67

4418

1.53

4424

1.38

23012

1.79

23018

1.60

23024

1.40

63-006

0.87

63-009

1.15

63,1-012

1.45

63,2-015

1.47

63,3-018

1.54

63,1-212

1.63

63,1-412

1.77

64-006

0.80

64-009

1.17

64-206

1.03

64-209

1.40

64-210

1.45

64,1-012

1.45

64,1-212

1.55

64,1-412

1.67

65-006

0.92

65-009

1.08

65-206

1.03

65-209

1.30

65-210

1.40

65,1-212

1.47

65,1-412

1.66

65,2-015

1.42

65,3-018

1.37

63A010

1.20

63A210

1.43

64A010

1.28

64A210

1.44

64A410

1.61

64,1-A212

1.54

64,2-A215

1.50