Similarly shaped airfoils to Rosner t=45.0 f=9.0, rN=0.6, te=16.8-14400 a=0.6
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D9.0%2C%20rN%3D0.6%2C%20te%3D16.8-14400%20a%3D0.6.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. NACA66-209
3. NACA67-209
4. NACA66-209 a=0.0
5. MH 24 9.01%
6. NACA66A209
7. NACA66-209 a=0.2
8. NACA66-209 a=0.8
9. NACA65A209
10. EPPLER 904
11. NACA66-209 a=0.5
12. NACA67-209 a=0.0
13. NACA66-209 a=0.6
14. NACA67A209
15. NACA67-209 a=0.2
16. NACA67-209 a=0.8
17. NACA67-209 a=0.5
18. NACA67-209 a=0.6
19. NACA66-109 a=0.6
20. GIII BL126
21. NACA65A210