Similarly shaped airfoils to NACA65-312 a=0.8
New! Bulk download of polars in Excel format: NACA65-312%20a%3D0.8.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. NACA64A312
3. NACA65-312 a=0.6
4. NACA63A312
5. NACA65A312
6. NACA64-312 a=0.8
7. NACA65-312 a=0.5
8. NACA65-312
9. GA 40-212
10. GA 40A212
11. NACA64-412
12. NACA64-312 a=0.6
13. GA 37A212
14. NACA65A311
15. NACA65(1)-412
16. NACA65-313 a=0.8
17. NACA65-311 a=0.8
18. GA 35A212
19. NACA64-312 a=0.5
20. NACA63-312 a=0.8
21. NACA64A311