Similarly shaped airfoils to NACA63-510 a=0.6
New! Bulk download of polars in Excel format: NACA63-510%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
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2. NACA63-510 a=0.5
3. NACA64-510 a=0.5
4. GA 35-410
5. GA 37-410
6. EPPLER E193gU-K24
7. S3024 9.84%
8. EPPLER 193
9. GA 35A410
10. NACA65-510 a=0.6
11. NACA63-510 a=0.8
12. S4061-096-84
13. NACA64-510 a=0.8
14. GA 37A410
15. NACA65-510 a=0.5
16. GA 40-410
17. GA 40A410
18. NACA63-511 a=0.6
19. NACA63-509 a=0.6
20. SD6080 (9.2%)
21. NACA64-509 a=0.6