Similarly shaped airfoils to NACA66(215)-416
New! Bulk download of polars in Excel format: NACA66%28215%29-416.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. NACA66A416
3. NACA66-416 a=0.8
4. NACA66-416
5. NACA66(2)-415
6. NACA66-416 a=0.6
7. NACA65A416
8. FX 38-153
9. NACA66-517
10. NACA66-515
11. NACA66A415
12. NACA66A417
13. NACA66-415 a=0.8
14. NACA66-417 a=0.8
15. NACA66-316 a=0.8
16. NACA66-416 a=0.5
17. EPPLER 664
18. NACA66-415
19. NACA66A316
20. NACA66-316 a=0.6
21. NACA65A417