Similarly shaped airfoils to NACA66-509 a=0.8
New! Bulk download of polars in Excel format: NACA66-509%20a%3D0.8.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. NACA66-609
3. NACA65A509
4. NACA67-509 a=0.8
5. NACA67A509
6. NACA65-509 a=0.8
7. NACA66-509 a=0.6
8. NACA65-609
9. NACA64A509
10. NACA66-510 a=0.8
11. NACA65A510
12. NACA65-510 a=0.8
13. NACA66A510
14. NACA66-610
15. NACA67-509 a=0.6
16. NACA63A509
17. NACA65-610
18. NACA66-709
19. NACA65-509 a=0.6
20. NACA66-509 a=0.5
21. NACA64A510