Similarly shaped airfoils to Rosner t=35.0 f=12.0, rN=1.1, te=14.0
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D12.0%2C%20rN%3D1.1%2C%20te%3D14.0.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.
2. NACA63A012
3. GA 35A012
4. GA 37A012
5. J5012 12%
6. NACA64-012A
7. GA 30-012
8. EPPLER 171
9. NACA0012
10. GA 30A012
11. N-13
12. N-14
13. NACA M3
14. NACA M3 (NACA-TR-221)
15. RAF 30
16. Horten 12.00% thick 0.00% camber
17. NACA64-012
18. bradshaw_baseline
19. EPPLER EA 6(-1)-012
20. GA 37-013
21. GA 40A012