Similarly shaped airfoils to NACA65-513 a=0.0
New! Bulk download of polars in Excel format: NACA65-513%20a%3D0.0.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. NACA65-413 a=0.2
3. NACA64-513 a=0.0
4. NACA64-513 a=0.2
5. NACA65-413 a=0.5
6. NACA65-514 a=0.0
7. NACA65-512 a=0.0
8. GA 40-313
9. AH 81-131
10. GA 40A313
11. NACA65-514 a=0.2
12. NACA64-514 a=0.0
13. GA 37A313
14. NACA63-513 a=0.0
15. NACA64-413 a=0.2
16. NACA65-413 a=0.0
17. NACA65-613 a=0.0
18. NACA64-514 a=0.2
19. EPPLER 231
20. NACA65-512 a=0.2
21. NACA65-412 a=0.2