Similarly shaped airfoils to NACA66-414
New! Bulk download of polars in Excel format: NACA66-414.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA66A314
3. NACA66-314 a=0.6
4. NACA66A414
5. NACA66-314 a=0.5
6. NACA65A314
7. NACA66-414 a=0.8
8. NACA66-415
9. NACA66-413
10. NACA66-314
11. NACA66-514
12. NACA66-313 a=0.8
13. NACA66A313
14. NACA66-315 a=0.8
15. NACA66A315
16. NACA65A414
17. NACA66-313 a=0.6
18. NACA66(2)-415
19. NACA65A315
20. NACA67-313 a=0.8
21. NACA66-315 a=0.6