Similarly shaped airfoils to NACA63A517
New! Bulk download of polars in Excel format: NACA63A517.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. NACA65-517 a=0.8
3. NACA65-617
4. NACA64-517 a=0.8
5. NACA63A518
6. NACA63A516
7. NACA64-617
8. NACA64A518
9. NACA64-518 a=0.8
10. NACA64-618
11. NACA64A516
12. GA 35A417
13. NACA63(420)-517
14. GA 37A417
15. NACA65-518 a=0.8
16. NACA63-517 a=0.8
17. NACA65-618
18. NACA63A417
19. NACA65A517
20. NACA63-617
21. NACA65-517 a=0.6