Similarly shaped airfoils to NACA65-614 a=0.5
New! Bulk download of polars in Excel format: NACA65-614%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. NACA64-614 a=0.5
3. AH 81-K-144/17
4. FX 78-K-140/20
5. NACA64-614 a=0.6
6. NACA65-615 a=0.5
7. NACA65-613 a=0.5
8. GA 40-614
9. FX 78-K-140 A/20
10. GA 40A614
11. AH 80-129
12. NACA65-615 a=0.6
13. GA 37A614
14. FX 84-W-140
15. AH 79-K-132/20
16. NACA64-615 a=0.5
17. NACA65-613 a=0.6
18. NACA63-614 a=0.5
19. NACA64-615 a=0.6
20. GA 35A614
21. EPPLER 434