Similarly shaped airfoils to NACA63-314 a=0.2
New! Bulk download of polars in Excel format: NACA63-314%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. NACA64-314 a=0.2
3. NACA64-314 a=0.0
4. GA 35-214
5. NACA63-414 a=0.0
6. GA 37-214
7. NACA63-314 a=0.5
8. NACA64-414 a=0.0
9. NACA64-314 a=0.5
10. NACA63-214 a=0.5
11. NACA63-315 a=0.2
12. NACA63-313 a=0.2
13. NACA63-214 a=0.6
14. NACA64-214 a=0.5
15. NACA63-313 a=0.0
16. NACA63-314 a=0.6
17. NACA64-313 a=0.2
18. NACA64-315 a=0.2
19. NACA63-315 a=0.0
20. NACA64-214 a=0.6
21. NACA64-314 a=0.6