Similarly shaped airfoils to NACA65-514 a=0.2
New! Bulk download of polars in Excel format: NACA65-514%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. NACA65-614 a=0.0
3. NACA64-514 a=0.2
4. NACA64-614 a=0.0
5. AH 79-K-135/20 B
6. NACA65-515 a=0.2
7. NACA65-513 a=0.2
8. NACA65-414 a=0.5
9. NACA64-514 a=0.0
10. NACA65-513 a=0.0
11. NACA65-615 a=0.0
12. NACA64-515 a=0.2
13. GA 40-314
14. GA 40A314
15. NACA65-515 a=0.0
16. NACA64-615 a=0.0
17. NACA63-514 a=0.2
18. FX 63-143
19. NACA65-414 a=0.2
20. NACA65-613 a=0.0
21. NACA65-614 a=0.2