Similarly shaped airfoils to NACA66-209 a=0.5
New! Bulk download of polars in Excel format: NACA66-209%20a%3D0.5.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=0.8
3. NACA66A209
4. NACA66-209 a=0.2
5. NACA66-209 a=0.0
6. NACA65A209
7. NACA67-209 a=0.5
8. NACA67-209 a=0.6
9. NACA66-209
10. EPPLER 904
11. NACA66-309 a=0.0
12. NACA65-209 a=0.5
13. NACA66-309
14. NACA65-209 a=0.6
15. NACA67-209 a=0.8
16. NACA67A209
17. NACA67-209 a=0.2
18. MH 24 9.01%
19. NACA65-209 a=0.8
20. NACA65-209 a=0.2
21. NACA67-209 a=0.0