Similarly shaped airfoils to Rosner t=35.0 f=13.0, rN=1.3, te=15.1-17600 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D13.0%2C%20rN%3D1.3%2C%20te%3D15.1-17600%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. NACA63A213
3. S8038 (13%)
4. NACA64A213
5. NACA64-213 a=0.5
6. NACA64-214 a=0.5
7. NACA64-214 a=0.6
8. NACA64-213 a=0.6
9. NACA65-213 a=0.5
10. NACA63-213 a=0.5
11. NACA64-213 a=0.2
12. NACA63-214 a=0.5
13. NACA63-213 a=0.6
14. NACA65-213 a=0.6
15. NACA63-214 a=0.6
16. NACA64-214 a=0.2
17. NACA64-214 a=0.8
18. NACA64-213 a=0.8
19. NACA65-213 a=0.2
20. Rosner t=35.0 f=14.0, rN=1.5, te=16.2-17600 a=0.4
21. Rosner t=35.0 f=12.0, rN=1.1, te=14.0-17600 a=0.4