Similarly shaped airfoils to NACA64-312
New! Bulk download of polars in Excel format: NACA64-312.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. NACA64-212 a=0.8
3. HQ 1.5/12
4. NACA64-212 a=0.6
5. NACA65-312
6. NACA63-212 a=0.8
7. NACA64-312 a=0.8
8. NACA63-212 a=0.6
9. GA 37-212
10. NACA64(1)-212
11. NACA63-312 a=0.8
12. NACA64-212 a=0.5
13. GA 35-212
14. NACA65(1)-212 a=0.6
15. NACA63-212 a=0.5
16. NACA63A312
17. HQ 1.5/11
18. NACA65-212 a=0.8
19. NACA63A212
20. HN-980
21. GA 35A212