Similarly shaped airfoils to Rosner t=45.0 f=12.0, rN=1.1, te=21.9


New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D12.0%2C%20rN%3D1.1%2C%20te%3D21.9.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.
1. NACA0012-64
2. AH 85-L-120/17
3. NACA0012-34
4. NACA66-012
5. LWK 80-120/K25
6. EPPLER 836 HYDROFOIL
7. S1012
8. SC(2)-0012
9. N-14
10. N-13
11. Rosner t=45.0 f=13.0, rN=1.3, te=23.6
12. Rosner t=45.0 f=11.0, rN=0.9, te=20.2
13. NACA/LANGLEY 0011SC SYMMETRICAL, SUPERCRITICAL
14. NACA M3
15. NACA M3 (NACA-TR-221)
16. GA 37A013
17. J5012 12%
18. GA 40A013
19. NACA66-112 a=0.0
20. NACA64-012A
21. GA 40-013