Canard Tip Airfoil Zero-lift Angle of Attack at M = 0

NACA Airfoil

Sectional Zero-Lift Angle-of-Attack,

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0006

0.0

0009

0.0

0012

0.0

1408

-0.8

1412

-1.1

2412

-2.0

2418

-2.8

2424

-1.8

4412

-3.8

4418

-3.8

4424

-3.8

23012

-1.4

23018

-1.2

23024

-0.8

63-006

0.0

63-009

0.0

63,1-012

0.0

63,2-015

0.0

63,3-018

0.0

63,1-212

-2.0

63,1-412

-2.8

64-006

0.0

64-009

0.0

64-206

-1.0

64-209

-1.5

64-210

-1.6

64,1-012

0.0

64,1-212

-1.3

64,1-412

-2.6

65-006

0.0

65-009

0.0

65-206

-1.6

65-209

-1.2

65-210

-1.6

65,1-212

-1.0

65,1-412

-3.0

65,2-015

0.0

65,3-018

0.0

63A010

0.0

63A210

-1.5

64A010

0.0

64A210

-1.5

64A410

-3.0

64,1-A212

-2.0

64,2-A215

-2.0