Similarly shaped airfoils to NACA66-414 a=0.6
New! Bulk download of polars in Excel format: NACA66-414%20a%3D0.6.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. NACA66-414 a=0.8
3. NACA66A414
4. NACA66-514
5. FX 79-K-144/17
6. NACA66-415 a=0.6
7. NACA66-413 a=0.6
8. NACA65A414
9. NLF-0414F
10. AH 79-K-143/18
11. NACA66-413 a=0.5
12. NACA66-415 a=0.5
13. NACA67-414 a=0.6
14. NACA67-413 a=0.6
15. NACA67-413 a=0.5
16. NACA67-414 a=0.5
17. NACA66-415 a=0.8
18. NACA66-413 a=0.8
19. NACA66A413
20. NACA66A514
21. NACA66A415