Similarly shaped airfoils to NACA64-513 a=0.6
New! Bulk download of polars in Excel format: NACA64-513%20a%3D0.6.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA64-513 a=0.5
3. GA 37-413
4. NACA63-513 a=0.5
5. GA 35-413
6. NACA65-513 a=0.6
7. GA 35A413
8. NACA64-513 a=0.8
9. GA 40-413
10. NACA65-513 a=0.5
11. GA 40A413
12. GA 37A413
13. NACA63-513 a=0.8
14. NACA64-514 a=0.6
15. NACA64-512 a=0.6
16. FX 84-W-127
17. NACA63-512 a=0.6
18. GA 35A412
19. NACA63-514 a=0.6
20. NACA64-613
21. NACA64-512 a=0.5