Similarly shaped airfoils to NACA66A420
New! Bulk download of polars in Excel format: NACA66A420.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. NACA66-520
3. NACA66-420 a=0.6
4. NACA66-420
5. NACA66-420 a=0.5
6. NACA66A419
7. NACA66-419 a=0.8
8. NACA66-519
9. NACA65A420
10. NACA66-320 a=0.8
11. NACA66-320 a=0.6
12. NACA66A320
13. NACA66-419 a=0.6
14. NACA66A520
15. NACA66-419
16. NACA66-620
17. NACA66-520 a=0.8
18. NACA66-320 a=0.5
19. NACA66-419 a=0.5
20. NACA66-319 a=0.8
21. NACA65A320