Similarly shaped airfoils to NACA66A612
New! Bulk download of polars in Excel format: NACA66A612.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. NACA66-712
3. NACA65A612
4. NACA67A612
5. NACA67-612 a=0.8
6. NACA66A613
7. NACA66-613 a=0.8
8. NACA66A611
9. NACA66-611 a=0.8
10. NACA67-712
11. NACA65A613
12. NACA67A611
13. NACA66-612 a=0.6
14. NACA67-611 a=0.8
15. NACA66-711
16. NACA66-713
17. NACA65-612 a=0.8
18. AH 88-K-130/20
19. NACA67-711
20. FX 74-130 WP1
21. NACA65-712