Similarly shaped airfoils to NACA65-410 a=0.8
New! Bulk download of polars in Excel format: NACA65-410%20a%3D0.8.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. NACA64A410
3. NACA63A410
4. NACA65A410
5. NACA64-410 a=0.8
6. NACA64-510
7. NACA65-410 a=0.6
8. NACA63-410 a=0.8
9. NACA63-510
10. NACA64-410 a=0.6
11. NACA66-410 a=0.8
12. NACA66A410
13. GA 40-310
14. GA 40A310
15. NACA65A409
16. NACA65-410 a=0.5
17. NACA66-510
18. NACA65-411 a=0.8
19. NACA65-409 a=0.8
20. GA 37A310
21. NACA65-410