NACA67-110 a=0.0
The Venkataraman airfoil fit was presented in AIAA-95-1875 by P. Venkataraman of the Rochester Institute of Technology.
The airfoil geometry is obtained through four Bezier curves, two for the upper surface (forward and aft), and two for the lower surface (forward and aft). This ease of construction makes it suitable for ease of use in CAD systems, and in airfoil shape optimization.
Selig-format DAT file: download
DXF file: download
Endpoints:
| Point | Coordinates |
|---|---|
| Leading edge point A | (0.000000, 0.000000) |
| Trailing edge C | (1.000074, -0.000880) |
| Upper point BU | (0.467299, 0.054837) |
| Lower point BL | (0.527516, -0.045375) |
| Upper Forward | Upper Rear | Lower Forward | Lower Rear |
|---|---|---|---|
| (0.000000, 0.000000) | (0.467299, 0.054837) | (0.000000, 0.000000) | (0.527516, -0.045375) |
| (0.000000, 0.029037) | (0.801377, 0.054837) | (0.000000, -0.037544) | (0.816995, -0.045375) |
| (0.212013, 0.054837) | (0.877955, 0.008775) | (0.431734, -0.045375) | (0.881106, -0.008610) |
| (0.467299, 0.054837) | (1.000074, -0.000880) | (0.527516, -0.045375) | (1.000074, -0.000880) |
Deviation from basic shape: 0.001167 (0.1167% of chord) = 1.2 mm on a 1 m chord or 0.056 in on a 48 in chord
| Segment | Deviation |
|---|---|
| Combined | 0.001167 (0.1167% of chord) |
| Upper (all) | 0.000320 (0.0320% of chord) |
| Upper Forward | 0.000273 (0.0273% of chord) |
| Upper Rear | 0.000320 (0.0320% of chord) |
| Lower (all) | 0.001167 (0.1167% of chord) |
| Lower Forward | 0.001167 (0.1167% of chord) |
| Lower Rear | 0.000345 (0.0345% of chord) |