Similarly shaped airfoils to NACA66-209 a=0.8
New! Bulk download of polars in Excel format: NACA66-209%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. NACA66-209 a=0.6
3. NACA66-209 a=0.5
4. NACA65A209
5. NACA66-209
6. NACA66-309
7. EPPLER 904
8. NACA67-209 a=0.8
9. NACA67A209
10. NACA67-209 a=0.6
11. NACA66-209 a=0.2
12. NACA65-209 a=0.8
13. NACA67-209 a=0.5
14. NACA67-209
15. NACA65-209 a=0.6
16. NACA66-209 a=0.0
17. NACA64A209
18. NACA65-209 a=0.5
19. NACA65-209
20. MH 24 9.01%
21. NACA65A210