Similarly shaped airfoils to NACA66A214
New! Bulk download of polars in Excel format: NACA66A214.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. NACA66-214 a=0.6
3. NACA66-214
4. NACA66-214 a=0.5
5. NACA66-314
6. NACA65A214
7. NACA66-214 a=0.2
8. NACA66-214 a=0.0
9. NACA66-215 a=0.8
10. NACA66A215
11. NACA66A213
12. NACA66-213 a=0.8
13. NACA66(2)-215
14. NACA66-215 a=0.6
15. NACA66-213 a=0.6
16. NACA66-213
17. NACA65A215
18. NACA66-215
19. NACA66-314 a=0.0
20. NACA66-215 a=0.5
21. NACA66-213 a=0.5