Similarly shaped airfoils to NACA63-713
New! Bulk download of polars in Excel format: NACA63-713.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. NACA63-613 a=0.8
3. NACA64-613 a=0.8
4. HQ 3.5/13
5. EPPLER 854
6. NACA63-714
7. NACA63-712
8. NACA63A613
9. NACA64-712
10. NACA64-714
11. HQ 3.5/12
12. NACA63-513 a=0.8
13. NACA63-614 a=0.8
14. NACA65-713
15. NACA63-613
16. EM J18 3212
17. HQ 3.0/13
18. NACA63-612 a=0.8
19. NACA63A612
20. NACA64-513 a=0.8
21. NACA64-614 a=0.8