Similarly shaped airfoils to NACA63-409 a=0.0
New! Bulk download of polars in Excel format: NACA63-409%20a%3D0.0.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. NACA63-409 a=0.2
3. NACA64-409 a=0.2
4. EPPLER 180
5. NACA65-409 a=0.0
6. NACA63-309 a=0.5
7. NACA64-309 a=0.5
8. NACA63-309 a=0.2
9. FX 69-H-083
10. NACA64-309 a=0.2
11. NACA65-409 a=0.2
12. MS1,9-8,7
13. NACA63-410 a=0.0
14. NACA63-309 a=0.6
15. B-29 TIP
16. NACA64-410 a=0.0
17. S6061 9%
18. NACA63-410 a=0.2
19. NACA64-309 a=0.6
20. MH 20 9.01%
21. RK40