Similarly shaped airfoils to NACA65-409
New! Bulk download of polars in Excel format: NACA65-409.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. NACA64-409
3. NACA64A309
4. NACA65-309 a=0.6
5. NACA64-309 a=0.8
6. NACA65A309
7. NACA63A309
8. NACA63-409
9. FX 80-080
10. S2048
11. NACA66-409
12. NACA64-309 a=0.6
13. SD2030-086-88
14. HQ-2.0/9 9.0% smoothed
15. NACA65-309 a=0.5
16. HQ 2.0/9
17. NACA63-309 a=0.8
18. NACA64A409
19. NACA66-309 a=0.8
20. NACA66A309
21. NACA63A409