Similarly shaped airfoils to Rosner t=35.0 f=16.0, rN=2.0, te=18.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D16.0%2C%20rN%3D2.0%2C%20te%3D18.4.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. NACA63A016
3. EPPLER 476
4. GA 30-016
5. GA 37A016
6. EPPLER 837 HYDROFOIL
7. NACA0016
8. Horten 16.00% thick 0.00% camber
9. GA 37-017
10. GA 30A016
11. GA 37-016
12. GA 35-017
13. NACA63A017
14. GA 35A017
15. Rosner t=35.0 f=17.0, rN=2.2, te=19.4
16. Rosner t=35.0 f=15.0, rN=1.7, te=17.3
17. GA 35-016
18. GA 30-015
19. EPPLER 477
20. GA 30A015
21. GA 40A016