Similarly shaped airfoils to Rosner t=45.0 f=16.0, rN=2.0, te=28.2


New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D16.0%2C%20rN%3D2.0%2C%20te%3D28.2.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. S1014
2. NACA66(215)-016
3. Rosner t=45.0 f=17.0, rN=2.2, te=29.7
4. Rosner t=45.0 f=15.0, rN=1.7, te=26.7
5. NACA66-116 a=0.0
6. GA 37A017
7. NACA66-116
8. GA 40A017
9. NACA66-116 a=0.2
10. NACA66-117 a=0.0
11. NACA66-117
12. NACA65A117
13. GA 40-017
14. NACA66-117 a=0.2
15. NACA66A116
16. NACA65A116
17. NACA66-116 a=0.8
18. NACA66-116 a=0.5
19. GA 37A016
20. NACA66-116 a=0.6
21. NACA66A117