Similarly shaped airfoils to NACA65(215)-114
New! Bulk download of polars in Excel format: NACA65%28215%29-114.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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. NACA65-114
3. NACA65-114 a=0.6
4. NACA65-114 a=0.5
5. NACA65-114 a=0.2
6. NACA65-114 a=0.0
7. NACA64A114
8. NACA63A114
9. NACA64-114 a=0.8
10. NACA64-114 a=0.6
11. NACA64-114
12. NACA65-214
13. NACA64-114 a=0.5
14. NACA65A114
15. NACA64-114 a=0.2
16. NACA64-114 a=0.0
17. NACA65-113 a=0.8
18. NACA65-214 a=0.0
19. NACA65-113
20. NACA65-113 a=0.6
21. NACA65-113 a=0.5