Similarly shaped airfoils to NACA66-520
New! Bulk download of polars in Excel format: NACA66-520.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. NACA66A420
3. NACA66-420 a=0.6
4. NACA66-519
5. NACA66-419 a=0.8
6. NACA66-420
7. NACA66A419
8. NACA66-620
9. NACA66A520
10. NACA66-420 a=0.5
11. NACA65A420
12. NACA66-520 a=0.8
13. NACA66-419 a=0.6
14. NACA66-320 a=0.8
15. NACA66-419
16. NACA66-320 a=0.6
17. NACA66A320
18. NACA66-419 a=0.5
19. NACA66-619
20. NACA66A519
21. NACA67-419 a=0.8