Horizontal Tail Root Airfoil Lift Curve Slope at M = 0 and Re = 9x10^6

See Graphic

NACA Airfoil

Sectional Lift Curve Slope,

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0006

6.1879

0009

6.2452

0010-34

5.7925

0010-35

5.1477

0012

6.2504

1408

6.2452

1410

6.1879

1412

6.1879

2412

6.0161

2415

6.0734

2418

5.9015

2421

5.9015

2424

5.6150

4412

6.0161

4415

6.0161

4418

6.0161

4421

5.9015

4424

5.7296

23012

6.1306

23015

6.1306

23018

5.9588

23021

5.9015

23024

5.5577

63-006

6.4171

63-009

6.3598

63-206

6.4171

63-209

6.3025

63-210

6.4744

63,1-012

6.6463

63,2-015

5.7296

63,3-018

5.7296

63,1-212

6.5317

63,1-412

6.7036

64-006

6.2452

64-009

6.3025

64-206

6.3025

64-209

6.1306

64-210

6.3025

64,1-012

6.3598

64,1-212

6.4744

64,1-412

6.4171

65-006

6.0161

65-009

6.1306

65-206

6.0161

65-209

6.0734

65-210

6.1879

65,1-012

6.3025

65,1-212

6.1879

65,1-412

6.3598

65,2-015

5.2385

65,3-018

5.6723

63A010

6.0161

63A210

5.9014

64A010

6.3025

64A210

6.0161

64A410

5.7296

64,1-A212

5.7296

64,2-A215

5.4431

Horizontal Tail Root Airfoil Lift Curve Slope at M = 0