Similarly shaped airfoils to NLF-0414F
New! Bulk download of polars in Excel format: nlf414f.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. NACA66-514
3. NACA66A414
4. NACA66-414 a=0.6
5. NACA65A414
6. NACA66-515
7. NACA66-415 a=0.8
8. NACA65-515
9. NACA66A415
10. NACA65-415 a=0.8
11. FX 79-K-144/17
12. NACA66(2)-415
13. NACA66-414 a=0.5
14. NACA65(2)-415
15. NACA66-414
16. NACA65-414 a=0.8
17. NACA65-514
18. NACA65A415
19. NACA66-415 a=0.6
20. NACA65-415 a=0.6
21. NACA66A514