Similarly shaped airfoils to NACA65A312
New! Bulk download of polars in Excel format: NACA65A312.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. NACA66A312
3. NACA66-312 a=0.8
4. NACA65-312 a=0.8
5. NACA66-412
6. NACA66-312 a=0.6
7. NACA65-412
8. NACA63A312
9. NACA65-312 a=0.6
10. NACA66-312
11. NACA65-312
12. NACA66-312 a=0.5
13. GA 37A212
14. NACA65-313 a=0.8
15. GA 40A212
16. NACA65-312 a=0.5
17. NACA65A313
18. NACA65A311
19. NACA64A313
20. NACA66A311
21. NACA66-311 a=0.8