Similarly shaped airfoils to Rosner t=35.0 f=17.0, rN=2.2, te=19.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D17.0%2C%20rN%3D2.2%2C%20te%3D19.4.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. GA 35A017
3. NACA63A017
4. GA 30-017
5. Horten 17.00% thick 0.00% camber
6. NACA0017
7. GA 37-018
8. NACA64-018
9. GA 37A017
10. GA 35-018
11. GA 37-017
12. NACA63A018
13. Rosner t=35.0 f=18.0, rN=2.5, te=20.5
14. Rosner t=35.0 f=16.0, rN=2.0, te=18.4
15. GA 30A017
16. GA 30-016
17. NACA63-018
18. GA 35A018
19. NACA63(3)-018
20. GA 35-017
21. GA 30A016