Similarly shaped airfoils to NACA64A510
New! Bulk download of polars in Excel format: NACA64A510.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. NACA65-510 a=0.8
3. NACA65A510
4. NACA65-610
5. NACA64-510 a=0.8
6. NACA64-610
7. NACA63-510 a=0.8
8. NACA63-610
9. HQ 3.0/10
10. NACA64-511 a=0.8
11. NACA65A509
12. NACA65-510 a=0.6
13. NACA64-611
14. NACA64A511
15. NACA64A509
16. NACA63A509
17. NACA66A510
18. GOE 595
19. NACA65-511 a=0.8
20. NACA66-510 a=0.8
21. GA 37A410