Similarly shaped airfoils to Rosner t=45.0 f=12.0, rN=1.1, te=21.9-13000 a=0.6
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D12.0%2C%20rN%3D1.1%2C%20te%3D21.9-13000%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. RC12-64C
3. HAWKER TEMPEST 61% SEMISPAN
4. NACA66-212
5. NACA66-212 a=0.0
6. NACA66(1)-212
7. NACA66-212 a=0.2
8. NACA66A212
9. NACA66-112 a=0.6
10. NACA66-112 a=0.5
11. NACA67-212
12. NACA66-212 a=0.8
13. NACA65A212
14. NACA66-112 a=0.8
15. NACA65A213
16. NACA66A112
17. AMSOIL2 RUTAN WING
18. NACA66-213
19. NACA66-212 a=0.5
20. NACA66-212 a=0.6
21. NACA 66,2-(1.8)12 A=.6 P-51 TIP