Similarly shaped airfoils to NACA65-520 a=0.2
New! Bulk download of polars in Excel format: NACA65-520%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. NACA65-520 a=0.0
3. NACA65-420 a=0.5
4. NACA65-519 a=0.2
5. NACA65-519 a=0.0
6. GA 40-320
7. NACA65-619 a=0.0
8. NACA65-420 a=0.2
9. NACA65-620 a=0.2
10. GA 40A320
11. NACA64-620 a=0.0
12. NACA64-520 a=0.2
13. NACA65-420 a=0.6
14. NACA65-520 a=0.5
15. NACA65-419 a=0.5
16. NACA65-421 a=0.5
17. GA 37A320
18. GA 40-319
19. NACA65-419 a=0.2
20. GA 40A319
21. NACA64-620 a=0.2