Similarly shaped airfoils to NACA65-513 a=0.5
New! Bulk download of polars in Excel format: NACA65-513%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. GA 40A413
3. NACA65-513 a=0.6
4. GA 37A413
5. NACA64-513 a=0.5
6. GA 35A413
7. NACA64-513 a=0.6
8. GA 37-413
9. NACA65-514 a=0.5
10. NACA65-512 a=0.5
11. GA 40-414
12. GA 40A414
13. AH 79-K-132/20
14. NACA65-514 a=0.6
15. NACA64-514 a=0.5
16. NACA65-512 a=0.6
17. NACA63-513 a=0.5
18. NACA65-613 a=0.2
19. GA 40A412
20. GA 40-412
21. GA 37A412