Similarly shaped airfoils to Rosner t=45.0 f=9.0, rN=0.6, te=16.8-13000 a=0.6
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D9.0%2C%20rN%3D0.6%2C%20te%3D16.8-13000%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
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. NACA66-209
3. NACA67-209
4. NACA66-209 a=0.0
5. NACA66-109 a=0.6
6. NACA66-109 a=0.5
7. NACA66-109 a=0.8
8. NACA66A109
9. NACA67-209 a=0.0
10. NACA66-209 a=0.2
11. NACA67-109 a=0.6
12. NACA65A109
13. NACA67-109 a=0.5
14. MH 24 9.01%
15. NACA66A209
16. NACA67-109 a=0.8
17. NACA67-209 a=0.2
18. NACA67A109
19. NACA65A209
20. GIII BL126
21. NACA66-209 a=0.8