Similarly shaped airfoils to NACA67(1)-215
New! Bulk download of polars in Excel format: NACA67%281%29-215.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. NACA67-215 a=0.8
3. NACA67-215
4. NACA67-215 a=0.6
5. NACA67-215 a=0.5
6. NACA67-215 a=0.2
7. NACA67-215 a=0.0
8. NACA67A214
9. NACA67-214 a=0.8
10. NACA67A216
11. NACA67-216 a=0.8
12. NACA67-214
13. NACA67-315 a=0.0
14. NACA67-214 a=0.6
15. NACA67-216
16. NACA67-216 a=0.6
17. NACA66(215)-216
18. NACA67-214 a=0.5
19. NACA67-216 a=0.5
20. NACA66(2)-215
21. NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT