Canard Leading Edge Radius to Chord Ratio at Canard Root Chord

See Graphic

NACA Airfoil

Sectional Lift Curve Slope,

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Leading Edge Radius

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0006

6.1879

0.400

0009

6.2452

0.890

0010

5.6339

1.100

0010-34

5.7925

0.272

0010-35

5.1477

0.272

0012

6.2504

1.580

0015

6.2556

2.480

0018

6.2608

3.560

1408

6.2452

0.705

1412

6.1879

1.580

2412

6.0161

1.587

2418

5.9015

3.570

2424

5.6150

6.347

4412

6.0161

1.580

4418

6.0161

3.560

4424

5.7296

6.330

23012

6.1306

1.580

23018

5.9588

3.560

23024

5.5577

6.330

63-006

6.4171

0.297

63-009

6.3598

0.631

63,1-012

6.6463

1.087

63,2-015

5.7296

1.594

63,3-018

5.7296

2.120

63,1-212

6.5317

1.087

63,1-412

6.7036

1.087

64-006

6.2452

0.256

64-009

6.7036

0.579

64-206

6.2452

0.256

64-209

6.1306

0.579

64-210

6.3025

0.720

64,1-012

6.3598

1.040

64,1-212

6.4744

1.040

64,1-412

6.4171

1.040

65-006

6.0161

0.240

65-009

6.1306

0.552

65-206

6.0161

0.240

65-209

6.0734

0.552

65-210

6.1879

0.687

65,1-012

6.3025

1.000

65,1-212

6.1879

1.000

65,1-412

6.3598

1.000

65,2-015

5.2385

1.505

65,3-018

5.6723

1.960

63A010

6.0161

0.740

63A210

5.9014

0.742

64A010

6.3025

0.687

64A210

6.0161

0.687

64A410

5.7296

0.687

64,1-A212

5.7296

0.994

64,2-A215

5.4431

1.561