Similarly shaped airfoils to Rosner t=45.0 f=14.0, rN=1.5, te=25.2


New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D14.0%2C%20rN%3D1.5%2C%20te%3D25.2.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. NACA66-015
2. Rosner t=45.0 f=15.0, rN=1.7, te=26.7
3. Rosner t=45.0 f=13.0, rN=1.3, te=23.6
4. GA 37A015
5. NACA64(2)-015A
6. LWK 80-150/K25
7. NACA66-114 a=0.0
8. GA 40A015
9. NACA66-114
10. GA 40-015
11. NACA65-015
12. NACA66-114 a=0.2
13. NACA66-115 a=0.0
14. NACA66-115
15. GA 37A014
16. NACA65A115
17. NACA66A114
18. NACA66-115 a=0.2
19. NACA67-114 a=0.0
20. NACA66-114 a=0.8
21. NACA65A114