Similarly shaped airfoils to NACA65-309 a=0.2


New! Bulk download of polars in Excel format: NACA65-309%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
Dynamic plotter New!
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.
1. NACA65-309 a=0.0
2. BOEING 707 .54 SPAN
3. KC-135 BL351.6
4. NACA64-309 a=0.2
5. BOEING 707 .99 SPAN
6. NACA64-309 a=0.0
7. NACA65-309 a=0.5
8. NACA63-309 a=0.2
9. NACA66-309 a=0.2
10. NACA63-309 a=0.0
11. NACA65-409 a=0.0
12. DP2.06/8.67_DS
13. NACA66-309 a=0.0
14. NACA64-309 a=0.5
15. DP1.87/9.07_DS
16. DP1.68/8.37_DS
17. NACA65-309 a=0.6
18. NACA M11 (NACA-TR-221)
19. NACA64-409 a=0.0
20. NACA M11
21. NACA64-310 a=0.2