Similarly shaped airfoils to NACA63-713 a=0.8
New! Bulk download of polars in Excel format: NACA63-713%20a%3D0.8.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. NACA63A713
3. NACA63-714 a=0.8
4. NACA63-712 a=0.8
5. NACA64-712 a=0.8
6. NACA64-714 a=0.8
7. NACA63A712
8. NACA64A713
9. NACA65-713 a=0.8
10. NACA63-713 a=0.6
11. EPPLER 210
12. NACA64A712
13. NACA64-713 a=0.6
14. NACA65-712 a=0.8
15. NACA63-613 a=0.8
16. NACA64-613 a=0.8
17. RAF 32
18. GA 35-613
19. GA 37-613
20. NACA63-613 a=0.6
21. NACA63-714 a=0.6