Similarly shaped airfoils to NACA66-311
New! Bulk download of polars in Excel format: NACA66-311.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. NACA66A311
3. NACA66-211 a=0.6
4. NACA66A211
5. NACA66-311 a=0.8
6. NACA66-211 a=0.5
7. NACA65A311
8. NACA65A211
9. NACA65-311
10. NACA66-311 a=0.6
11. NACA66-312
12. NACA66-310
13. NACA67A311
14. NACA66-311 a=0.5
15. NACA66-311 a=0.0
16. LOCKHEED C-141 BL610.61
17. P-51D TIP (BL215)
18. NACA67-211 a=0.8
19. NACA66-211
20. NACA66-411
21. NACA66-311 a=0.2