Similarly shaped airfoils to Rosner t=35.0 f=18.0, rN=2.5, te=20.5
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D18.0%2C%20rN%3D2.5%2C%20te%3D20.5.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. NACA63A018
3. GA 30-018
4. Horten 18.00% thick 0.00% camber
5. GA 37-019
6. NACA0018
7. GA 35-019
8. GA 37-018
9. Rosner t=35.0 f=17.0, rN=2.2, te=19.4
10. GA 37A018
11. GA 30-017
12. GA 35-018
13. NACA64-018
14. GA 30A018
15. GA 35A019
16. NACA63(3)-018
17. NACA63-018
18. GA 30A017
19. NACA64-119 a=0.0
20. US1000ROOT (Great Planes R/C Ultra-Sport 1000)
21. NACA64-119