Similarly shaped airfoils to SB96VS 9.75/1.25
New! Bulk download of polars in Excel format: SB96VS%209.75_1.25.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. TP-CIEL-S
3. NACA64-310
4. HQ 1.5/10
5. NACA63-310
6. EM CY 1016 1510
7. RG 14 9.5%
8. NACA64-210 a=0.8
9. NACA64-210 a=0.6
10. NACA63A210
11. NACA63-210 a=0.8
12. RG 14 9%
13. NACA64-210 a=0.5
14. NACA63-210 a=0.6
15. NACA65-310
16. NACA64A210
17. AIR 100-2 Acro MM 576 1999
18. GA 35A210
19. NACA63-210 a=0.5
20. GA 37A210
21. NACA65-210 a=0.8