Similarly shaped airfoils to NACA65A216
New! Bulk download of polars in Excel format: NACA65A216.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. NACA66-216 a=0.8
3. NACA66A216
4. NACA66-216 a=0.6
5. NACA66(215)-216
6. NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT
7. NACA65-216 a=0.8
8. NACA66-216
9. NACA66-216 a=0.5
10. NACA65A217
11. NACA65A215
12. NACA65-216 a=0.6
13. NACA66-316
14. NACA65-216
15. NACA65-216 a=0.5
16. NACA64A217
17. NACA65-217 a=0.8
18. NACA66A215
19. NACA66-215 a=0.8
20. NACA66(215)-216 a=0.6
21. NACA66(215)-216 a=0