Similarly shaped airfoils to Rosner t=35.0 f=18.0, rN=2.5, te=20.5-19500 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D18.0%2C%20rN%3D2.5%2C%20te%3D20.5-19500%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. NACA63A218
3. Rosner t=35.0 f=17.0, rN=2.2, te=19.4-19500 a=0.4
4. GA 35A218
5. Rosner t=35.0 f=17.0, rN=2.2, te=19.4-17600 a=0.4
6. NACA2318
7. NACA2418
8. NACA64-319
9. NACA64-319 a=0.2
10. NACA64-219 a=0.6
11. NACA63A318
12. NACA64-219 a=0.5
13. GA 30-218
14. NACA64-319 a=0.5
15. NACA63-319
16. NACA63-219 a=0.6
17. NACA63-219 a=0.5
18. NACA63-319 a=0.2
19. NACA64-318
20. NACA64-319 a=0.0
21. GA 37-219