Similarly shaped airfoils to YS-915


New! Bulk download of polars in Excel format: ys915.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. EPPLER 904
2. NACA65A209
3. NACA66-209 a=0.8
4. NACA66A209
5. NACA66-309
6. NACA65A210
7. NACA67-209 a=0.8
8. NACA67A209
9. NACA0010-34 a=0.8 c(li)=0.2
10. GOE 599
11. NACA64A210
12. NACA64A209
13. NACA65-210 a=0.8
14. NACA66-210 a=0.8
15. NACA66-209
16. NACA65-310
17. NACA66A210
18. NACA63A210
19. NACA66-310
20. NACA63A209
21. NACA65-209 a=0.8