Similarly shaped airfoils to NACA66A216
New! Bulk download of polars in Excel format: NACA66A216.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(215)-216
3. NACA66-216 a=0.6
4. NACA66-216
5. NACA66-216 a=0.5
6. NACA66-316
7. NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT
8. NACA66(215)-216 a=0.6
9. NACA66(215)-216 a=0
10. NACA66-216 a=0.2
11. NACA65A216
12. NACA66-216 a=0.0
13. NACA66-217 a=0.8
14. NACA66A217
15. NACA66A215
16. NACA66-215 a=0.8
17. NACA66(2)-215
18. NACA66-217 a=0.6
19. NACA66-215 a=0.6
20. NACA66-215
21. NACA66-316 a=0.0