Similarly shaped airfoils to Rosner t=45.0 f=13.0, rN=1.3, te=23.6-13000 a=0.6


New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D13.0%2C%20rN%3D1.3%2C%20te%3D23.6-13000%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.
1. Rosner t=45.0 f=13.0, rN=1.3, te=23.6-14400 a=0.6
2. NACA66-213
3. LOCKHEED C-141 BL0
4. LOCKHEED C-141 BL113.6
5. NACA66-213 a=0.0
6. NACA66-213 a=0.2
7. NACA66A213
8. NACA65A214
9. NACA66-213 a=0.8
10. NACA65A213
11. NACA66-113 a=0.6
12. NACA66-214
13. NACA66-213 a=0.5
14. NACA66-113 a=0.5
15. NACA66-213 a=0.6
16. Rosner t=45.0 f=14.0, rN=1.5, te=25.2-13000 a=0.6
17. Rosner t=45.0 f=12.0, rN=1.1, te=21.9-13000 a=0.6
18. NACA66-113 a=0.8
19. Rosner t=45.0 f=14.0, rN=1.5, te=25.2-14400 a=0.6
20. NACA67-213
21. NACA66A113