Similarly shaped airfoils to SG6041_PSO


New! Bulk download of polars in Excel format: SG6041_PSO.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
Dynamic plotter New!
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.

1. SG6042
2. NACA63A610
3. RAF 32 MOD
4. NACA64A610
5. HQ 3.5/10
6. MH 116 9.84%
7. GOE 547
8. NACA64-611 a=0.8
9. NACA63A611
10. GOE 546
11. NACA65-610 a=0.8
12. EPPLER 66
13. NACA65-710
14. NACA64-610 a=0.8
15. NACA64-711
16. NACA64A611
17. NACA64-710
18. NACA65A610
19. NACA63-611 a=0.8
20. PSU 94-097 (AIAA 2001-2478)
21. NACA63-610 a=0.8