Similarly shaped airfoils to NACA66-519
New! Bulk download of polars in Excel format: NACA66-519.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. NACA66A419
3. NACA66-419 a=0.6
4. FX 78-PK-188/20
5. NACA66-520
6. NACA66-518
7. NACA66-418 a=0.8
8. NACA66-419
9. NACA66A418
10. NACA65A419
11. NACA66-619
12. NACA66-420 a=0.8
13. NACA66-419 a=0.5
14. NACA66A519
15. NACA66A420
16. NACA66(3)-418
17. NACA66-519 a=0.8
18. NACA66-418 a=0.6
19. NACA65A420
20. NACA66-420 a=0.6
21. NACA66-319 a=0.8