Similarly shaped airfoils to NACA64-513 a=0.5
New! Bulk download of polars in Excel format: NACA64-513%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
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. GA 37-413
3. NACA64-513 a=0.6
4. NACA63-513 a=0.6
5. GA 35-413
6. GA 35A413
7. NACA65-513 a=0.5
8. GA 40-413
9. GA 40A413
10. GA 37A413
11. NACA65-513 a=0.6
12. NACA64-514 a=0.5
13. NACA64-512 a=0.5
14. GA 35A412
15. GA 37-414
16. NACA63-512 a=0.5
17. NACA63-514 a=0.5
18. NACA64-514 a=0.6
19. FX 84-W-127
20. NACA65-512 a=0.5
21. GA 37A412