Similarly shaped airfoils to NACA66-709 a=0.8
New! Bulk download of polars in Excel format: NACA66-709%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. NACA65A709
3. NACA67-709 a=0.8
4. NACA67A709
5. NACA65-709 a=0.8
6. NACA64A709
7. NACA66-710 a=0.8
8. NACA65-710 a=0.8
9. NACA65A710
10. NACA66A710
11. NACA63A709
12. NACA66-709 a=0.6
13. NACA64A710
14. NACA64-709 a=0.8
15. NACA67-709 a=0.6
16. NACA66-609 a=0.8
17. NACA63A710
18. NACA64-710 a=0.8
19. FX 74-080
20. NACA65-709 a=0.6
21. NACA66-609 a=0.6