Similarly shaped airfoils to NACA63A115
New! Bulk download of polars in Excel format: NACA63A115.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. NACA65-115 a=0.8
3. NACA65-115 a=0.6
4. NACA65-115
5. NACA64-115 a=0.8
6. NACA65-115 a=0.5
7. NACA64-115 a=0.6
8. NACA64-115
9. NACA64-115 a=0.5
10. NACA65-115 a=0.2
11. NACA65-115 a=0.0
12. NACA64-115 a=0.2
13. NACA64-116 a=0.8
14. NACA64-115 a=0.0
15. NACA64-116 a=0.6
16. NACA64-116
17. NACA64-116 a=0.5
18. NACA63A116
19. NACA63A114
20. NACA64A116
21. NACA64-116 a=0.2