Similarly shaped airfoils to Rosner t=35.0 f=11.0, rN=0.9, te=12.8-19500 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D11.0%2C%20rN%3D0.9%2C%20te%3D12.8-19500%20a%3D0.4.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. BOEING-VERTOL VR-1
3. LOCKHEED C-5A BL1256
4. NACA63A211
5. NACA64-211 a=0.5
6. NACA64-211 a=0.6
7. NACA65-211 a=0.5
8. NACA64A211
9. NACA65-211 a=0.6
10. NACA63-211 a=0.5
11. NACA64-212 a=0.5
12. NACA63-211 a=0.6
13. NACA64-212 a=0.6
14. GA 35A211
15. HQ 1.5/11
16. NACA64-311 a=0.0
17. NACA64-211 a=0.2
18. NACA63-212 a=0.5
19. NACA64-211 a=0.8
20. NACA65-211 a=0.2
21. NACA63-212 a=0.6