See Graphic
NACA Airfoil |
Sectional Lift Curve Slope,
|
Leading Edge Radius
|
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 |
0.158 |
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 |
6.3025 |
0.579 |
64-206 |
6.3025 |
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 |