Similarly shaped airfoils to NACA63-309 a=0.6
New! Bulk download of polars in Excel format: NACA63-309%20a%3D0.6.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. NACA63-309 a=0.5
3. NACA64-309 a=0.5
4. NACA63-309 a=0.8
5. NACA64-309 a=0.8
6. MS1,9-8,7
7. NACA63-409
8. HQ 2.0/9
9. HQ-2.0/9 9.0% smoothed
10. S6061 9%
11. NACA64-409
12. HN-450S
13. NACA65-309 a=0.6
14. NACA65-309 a=0.5
15. NACA63A309
16. HN-450
17. HN-1036
18. HN-801BASIC
19. HN-354A
20. HN-350M01
21. HN-184