Similarly shaped airfoils to NACA66-309 a=0.5
New! Bulk download of polars in Excel format: NACA66-309%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
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2. DP2.06/8.67_DS
3. DP2.05/8.65_DS
4. NACA67-309 a=0.5
5. NACA66-309 a=0.8
6. DP1.87/9.07_DS
7. NACA66A309
8. NACA66-309 a=0.2
9. NACA67-309 a=0.6
10. DP2.00/8.55_DS
11. NACA66-409 a=0.0
12. NACA65-309 a=0.5
13. NACA65-309 a=0.6
14. NACA65A309
15. NACA66-409
16. DP1.82/8.21_DS
17. BOEING 707 .99 SPAN
18. NACA66-309 a=0.0
19. NACA67-309 a=0.8
20. NACA67A309
21. NACA66-409 a=0.2