Similarly shaped airfoils to NACA67-709
New! Bulk download of polars in Excel format: NACA67-709.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. NACA67-609 a=0.8
3. NACA66-709
4. NACA66A609
5. NACA66-609 a=0.8
6. NACA66-710
7. NACA67-710
8. NACA66A610
9. NACA67-509 a=0.8
10. NACA65A609
11. NACA66-610 a=0.8
12. NACA67A610
13. NACA67-610 a=0.8
14. NACA65A610
15. NACA67A509
16. NACA66-509 a=0.8
17. NACA66-609
18. NACA67-609 a=0.6
19. NACA67-509 a=0.6
20. NACA66A509
21. NACA65-710