Similarly shaped airfoils to Rosner t=35.0 f=12.0, rN=1.1, te=14.0-19500 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D12.0%2C%20rN%3D1.1%2C%20te%3D14.0-19500%20a%3D0.4.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
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2. NACA63A212
3. S8052 (11.88%)
4. NACA64-212 a=0.5
5. NACA64-212 a=0.6
6. NACA64A212
7. NACA64-213 a=0.5
8. NACA65-212 a=0.5
9. NACA64-213 a=0.6
10. NACA65-212 a=0.6
11. NACA65(1)-212 a=0.6
12. NACA63-212 a=0.5
13. GA 35A212
14. HQ 1.5/12
15. NACA63-212 a=0.6
16. HQ 1.0/12
17. NACA2312
18. NACA64-312 a=0.0
19. NACA63-213 a=0.5
20. NACA64-313 a=0.0
21. NACA2412