Similarly shaped airfoils to NACA65A210
New! Bulk download of polars in Excel format: NACA65A210.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA66A210
3. NACA66-210 a=0.8
4. NACA65-210 a=0.8
5. NACA66-210 a=0.6
6. NACA0010-34 a=0.8 c(li)=0.2
7. NACA65-210 a=0.6
8. NACA66-210
9. NACA65-210
10. NACA63A210
11. NACA66-210 a=0.5
12. NACA65-210 a=0.5
13. HAWKER TEMPEST 96.77% SEMISPAN
14. NACA66-310
15. NACA65-310
16. NACA66-210 a=0.2
17. NACA65-211 a=0.8
18. NACA65-210 a=0.2
19. MH 24 9.01%
20. NACA64A211
21. EPPLER 904