Similarly shaped airfoils to NACA64-313 a=0.5
New! Bulk download of polars in Excel format: NACA64-313%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. NACA63-313 a=0.5
3. GA 37-213
4. NACA63-313 a=0.6
5. GA 35-213
6. NACA64-313 a=0.8
7. NACA65-313 a=0.5
8. GA 35A213
9. NACA64-413 a=0.0
10. NACA64-313 a=0.2
11. NACA63-313 a=0.8
12. NACA65-313 a=0.6
13. GA 40-213
14. NACA63-413 a=0.0
15. GA 40A213
16. NACA63-313 a=0.2
17. GA 37A213
18. NACA64-413
19. S8055 (12%)
20. NACA64-413 a=0.2
21. NACA63-413