Similarly shaped airfoils to NACA64-512 a=0.8
New! Bulk download of polars in Excel format: NACA64-512%20a%3D0.8.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. NACA64-612
3. NACA63-612
4. NACA63A512
5. NACA65-512 a=0.8
6. NACA64A512
7. NACA65-612
8. HQ 3.0/12
9. NACA64-512 a=0.6
10. NACA63A511
11. NACA63-512 a=0.6
12. NACA64-513 a=0.8
13. NACA64-511 a=0.8
14. EM J18 3012 DrW r1,2
15. NACA64A511
16. EPPLER 853
17. NACA63-511 a=0.8
18. NACA63-513 a=0.8
19. GA 37-412
20. NACA64-613
21. NACA65-511 a=0.8