Similarly shaped airfoils to NACA65-410 a=0.2
New! Bulk download of polars in Excel format: NACA65-410%20a%3D0.2.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. NACA64-410 a=0.2
3. NACA64-410 a=0.0
4. GA 40-310
5. NACA65-510 a=0.0
6. GA 40A310
7. NACA63-410 a=0.2
8. GA 37A310
9. DP2.47/9.48_DS
10. NACA64-510 a=0.0
11. NACA66-410 a=0.2
12. GA 35A310
13. NACA63-410 a=0.0
14. NACA65-411 a=0.2
15. NACA65-409 a=0.2
16. NACA65-410 a=0.5
17. NACA65-310 a=0.5
18. NACA66-410 a=0.0
19. NACA64-411 a=0.2
20. GA 37-310
21. NACA66-409 a=0.2