Similarly shaped airfoils to NACA64-314
New! Bulk download of polars in Excel format: NACA64-314.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. NACA64-214 a=0.8
3. NACA64-214 a=0.6
4. NACA63-214 a=0.8
5. NACA64-314 a=0.8
6. NACA63-214 a=0.6
7. NACA64-214 a=0.5
8. NACA65-314
9. NACA63-314 a=0.8
10. GA 37-214
11. NACA63-214 a=0.5
12. GA 35-214
13. NACA64-315
14. NACA64-313
15. NACA64-314 a=0.6
16. NACA65-214 a=0.8
17. NACA63A214
18. NACA63A314
19. NACA63-313
20. NACA65-214 a=0.6
21. NACA63-315