Similarly shaped airfoils to NACA65-309 a=0.8
New! Bulk download of polars in Excel format: NACA65-309%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. NACA65-409
3. NACA63A309
4. NACA65A309
5. NACA65-309 a=0.6
6. NACA64-309 a=0.8
7. NACA64-409
8. NACA65-309 a=0.5
9. NACA64-309 a=0.6
10. NACA63-309 a=0.8
11. NACA65-309
12. NACA66-309 a=0.8
13. NACA66A309
14. NACA63-409
15. S2048
16. NACA64-309 a=0.5
17. NACA63-309 a=0.6
18. NACA64-309
19. DP1.79/8.37_DS
20. HQ-2.0/9 9.0% smoothed
21. NACA66-409