Similarly shaped airfoils to Rosner t=35.0 f=13.0, rN=1.3, te=15.1-19500 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D13.0%2C%20rN%3D1.3%2C%20te%3D15.1-19500%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
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2. NACA63A213
3. S8038 (13%)
4. NACA64-213 a=0.5
5. NACA64-214 a=0.5
6. NACA64-213 a=0.6
7. NACA64A213
8. GA 35A213
9. NACA64-214 a=0.6
10. NACA65-213 a=0.5
11. NACA63-213 a=0.5
12. NACA64-313 a=0.0
13. NACA64-314 a=0.0
14. NACA65-213 a=0.6
15. NACA63-213 a=0.6
16. NACA63-214 a=0.5
17. NACA63-214 a=0.6
18. Rosner t=35.0 f=14.0, rN=1.5, te=16.2-19500 a=0.4
19. Rosner t=35.0 f=12.0, rN=1.1, te=14.0-19500 a=0.4
20. GA 37A213
21. GA 30-213