Similarly shaped airfoils to NACA64-410 a=0.8
New! Bulk download of polars in Excel format: NACA64-410%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. NACA64-510
3. NACA63-510
4. NACA63A410
5. NACA65-410 a=0.8
6. NACA64A410
7. NACA65-510
8. NACA64-410 a=0.6
9. HQ 2.5/10
10. NACA63-410 a=0.6
11. EM J8 2510 DrW
12. NACA63A409
13. NACA65-410 a=0.6
14. EM J18 2310
15. GA 37-310
16. EPPLER 222
17. NACA64A409
18. NACA64-410 a=0.5
19. HN-1023
20. NACA64-411 a=0.8
21. NACA64-409 a=0.8