Similarly shaped airfoils to NACA63-616
New! Bulk download of polars in Excel format: NACA63-616.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (6) | 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. NACA64-616
3. NACA64-516 a=0.8
4. NACA63-617
5. NACA63-615
6. NACA63-515 a=0.8
7. NACA63-517 a=0.8
8. SG6040
9. EM J18 3015 DrW r0,8
10. NACA63-516 a=0.6
11. NACA64-615
12. HQ 3.0/15
13. NACA64-617
14. NACA63-516
15. NACA63-716
16. GA 35-416
17. NACA64-515 a=0.8
18. NACA64-716
19. NACA64-517 a=0.8
20. NACA64-516 a=0.6
21. EM J18 2515 DrW r0,8