Similarly shaped airfoils to NACA65-614 a=0.6
New! Bulk download of polars in Excel format: NACA65-614%20a%3D0.6.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. NACA64-614 a=0.6
3. AH 81-K-144/17
4. GA 40-614
5. GA 40A614
6. NACA65-615 a=0.6
7. NACA65-613 a=0.6
8. NACA64-614 a=0.5
9. NACA65-614 a=0.8
10. FX 84-W-140
11. GA 37A614
12. NACA65-613 a=0.5
13. NACA64-615 a=0.6
14. NACA65-615 a=0.5
15. FX 78-K-140 A/20
16. NACA63-614 a=0.6
17. GA 35A614
18. NACA64A614
19. FX 78-K-140/20
20. AH 80-129
21. NACA66-613 a=0.6