Similarly shaped airfoils to NACA0010-34 a=0.8 c(li)=0.2
New! Bulk download of polars in Excel format: NACA001034a08cli0.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. NACA66-210 a=0.8
3. NACA66A210
4. NACA66-210 a=0.6
5. MH 25 9.98%
6. NACA66-310
7. NACA67-210 a=0.8
8. NACA66-210 a=0.5
9. NACA67A210
10. NACA67-210 a=0.6
11. NACA66-210
12. NACA65A211
13. NACA67-210 a=0.5
14. EPPLER 904
15. GOE 599
16. MH 24 9.01%
17. NACA64A210
18. NACA67-210
19. NACA66-210 a=0.2
20. HAWKER TEMPEST 96.77% SEMISPAN
21. NACA66-211 a=0.8