Similarly shaped airfoils to NACA66-309 a=0.2
New! Bulk download of polars in Excel format: NACA66-309%20a%3D0.2.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. NACA67-309 a=0.2
3. NACA66-309 a=0.5
4. DP1.87/9.07_DS
5. BOEING 707 .54 SPAN
6. NACA67-309 a=0.0
7. KC-135 BL351.6
8. DP2.06/8.67_DS
9. NACA65-309 a=0.2
10. BOEING 707 .99 SPAN
11. NACA66-409 a=0.0
12. NACA65-309 a=0.0
13. DP2.05/8.65_DS
14. NACA66-309 a=0.6
15. DP1.68/8.37_DS
16. NACA67-309 a=0.5
17. DP1.77/8.23_DS
18. NACA66-310 a=0.2
19. DP1.82/8.21_DS
20. NACA65-310 a=0.2
21. NACA66-209 a=0.5