Similarly shaped airfoils to NACA67A312
New! Bulk download of polars in Excel format: NACA67A312.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. NACA67-312 a=0.6
3. NACA67-312 a=0.5
4. NACA66A312
5. NACA66-312 a=0.8
6. NACA67-313 a=0.8
7. NACA67A313
8. NACA67A311
9. NACA67-311 a=0.8
10. NACA66A313
11. NACA66-312 a=0.6
12. NACA66-412
13. NACA66-313 a=0.8
14. MH 27 11.99%
15. NACA66-312
16. NACA67-313 a=0.6
17. NACA67-311 a=0.6
18. NACA67-312 a=0.2
19. NACA66-413
20. NACA66-312 a=0.5
21. NACA67-212 a=0.6