Similarly shaped airfoils to NACA65A218
New! Bulk download of polars in Excel format: NACA65A218.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. NACA66-218 a=0.8
3. NACA66A218
4. NACA65A219
5. NACA65A217
6. NACA66(3)-218
7. NACA66-218 a=0.6
8. NACA66-218
9. NACA66-218 a=0.5
10. NACA66-318
11. NACA65-218 a=0.8
12. AS5048 (18%)
13. NACA65-218 a=0.6
14. NACA64A219
15. NACA65(3)-218
16. NACA66-217 a=0.8
17. NACA66A217
18. NACA65-219 a=0.8
19. NACA65-218
20. NACA65-218 a=0.5
21. NACA65A118