Similarly shaped airfoils to NACA63-612 a=0.5
New! Bulk download of polars in Excel format: NACA63-612%20a%3D0.5.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. NACA63-612 a=0.6
3. NACA64-612 a=0.6
4. GA 35-612
5. GA 37-612
6. NACA63-613 a=0.5
7. NACA63-611 a=0.5
8. NACA65-612 a=0.5
9. NACA64-611 a=0.5
10. NACA64-613 a=0.5
11. NACA63-613 a=0.6
12. NACA63-611 a=0.6
13. GA 35A612
14. NACA64-613 a=0.6
15. NACA65-612 a=0.6
16. NACA64-611 a=0.6
17. S4158
18. NACA65-611 a=0.5
19. NACA63-712 a=0.2
20. GA 37A612
21. GA 35-613