Similarly shaped airfoils to NACA65-620 a=0.5
New! Bulk download of polars in Excel format: NACA65-620%20a%3D0.5.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. NACA65-619 a=0.5
3. NACA65-619 a=0.6
4. GA 40-420
5. GA 40A420
6. NACA64-620 a=0.5
7. NACA65-720 a=0.2
8. NACA64-620 a=0.6
9. NACA65-520 a=0.6
10. NACA65-520 a=0.5
11. NACA65-720 a=0.5
12. GA 37A420
13. NACA65-620 a=0.8
14. GA 40-419
15. GA 40A419
16. NACA65-720 a=0.0
17. GA 35A420
18. GA 37-420
19. NACA64-720 a=0.5
20. NACA65-719 a=0.2
21. NACA65-720 a=0.6