Similarly shaped airfoils to Rosner t=45.0 f=12.0, rN=1.1, te=21.9-14400 a=0.6
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D12.0%2C%20rN%3D1.1%2C%20te%3D21.9-14400%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. RC12-64C
3. HAWKER TEMPEST 61% SEMISPAN
4. NACA66-212
5. NACA66(1)-212
6. NACA66A212
7. NACA66-212 a=0.8
8. NACA66-212 a=0.2
9. NACA66-212 a=0.0
10. NACA65A212
11. NACA66-212 a=0.5
12. NACA66-212 a=0.6
13. NACA 66,2-(1.8)12 A=.6 P-51 TIP
14. NACA65A213
15. NACA67-212
16. NACA66-213
17. MH 17
18. AMSOIL2 RUTAN WING
19. NACA67A212
20. LOCKHEED C-5A BL488.2
21. Rosner t=45.0 f=13.0, rN=1.3, te=23.6-14400 a=0.6