Similarly shaped airfoils to NACA66-419
New! Bulk download of polars in Excel format: NACA66-419.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. NACA66A319
3. NACA66-319 a=0.6
4. NACA66A419
5. NACA66-319 a=0.5
6. NACA66-419 a=0.8
7. NACA66-319
8. NACA66-420
9. NACA66-418
10. NACA66-519
11. NACA66-318 a=0.8
12. NACA65A319
13. NACA66A318
14. NACA66-320 a=0.8
15. NACA66A320
16. NACA66-318 a=0.6
17. NACA66-320 a=0.6
18. NACA66A420
19. NACA65A320
20. NACA66-318 a=0.5
21. NACA66-419 a=0.6