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
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
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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