Similarly shaped airfoils to NACA67A213
New! Bulk download of polars in Excel format: NACA67A213.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. NACA67-213 a=0.6
3. NACA67-213
4. NACA67-213 a=0.5
5. NACA67-213 a=0.2
6. NACA67-213 a=0.0
7. NACA66A213
8. NACA67-214 a=0.8
9. NACA67A214
10. NACA67A212
11. NACA66-213 a=0.8
12. NACA67-212 a=0.8
13. NACA67-214 a=0.6
14. NACA66-213 a=0.6
15. NACA67-212 a=0.6
16. NACA67-313 a=0.0
17. NACA66-213
18. NACA67-212
19. NACA67-214
20. NACA66A214
21. NACA66-214 a=0.8