Similarly shaped airfoils to NACA65-312 a=0.5
New! Bulk download of polars in Excel format: NACA65-312%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. GA 40-212
3. GA 40A212
4. GA 37A212
5. NACA64-312 a=0.5
6. NACA65-312 a=0.8
7. NACA64-312 a=0.6
8. NACA65-312 a=0.2
9. NACA65-412 a=0.0
10. GA 35A212
11. NACA64A312
12. NACA65-412
13. GA 37-212
14. NACA65-412 a=0.2
15. NACA63A312
16. NACA65-313 a=0.5
17. NACA65-311 a=0.5
18. NACA64-312 a=0.8
19. NACA65A312
20. NACA63-312 a=0.5
21. NACA65-313 a=0.6