Similarly shaped airfoils to NACA66A209
New! Bulk download of polars in Excel format: NACA66A209.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
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2. NACA66-209 a=0.6
3. NACA66-209
4. NACA65A209
5. NACA66-209 a=0.5
6. EPPLER 904
7. NACA67A209
8. NACA67-209 a=0.8
9. NACA66-309
10. NACA66-209 a=0.2
11. NACA67-209 a=0.6
12. NACA65-209 a=0.8
13. NACA67-209
14. NACA67-209 a=0.5
15. NACA66-209 a=0.0
16. NACA65-209 a=0.6
17. NACA64A209
18. NACA65-209
19. NACA65-209 a=0.5
20. MH 24 9.01%
21. NACA65A210