Similarly shaped airfoils to Rosner t=30.0 f=14.0, rN=1.5, te=13.2-21700 a=0.3
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D14.0%2C%20rN%3D1.5%2C%20te%3D13.2-21700%20a%3D0.3.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. Rosner t=30.0 f=15.0, rN=1.7, te=14.1-21700 a=0.3
3. Rosner t=30.0 f=13.0, rN=1.3, te=12.3-21700 a=0.3
4. NACA63-314 a=0.0
5. NACA63-314 a=0.2
6. Rosner t=30.0 f=15.0, rN=1.7, te=14.1-24325 a=0.3
7. Rosner t=30.0 f=13.0, rN=1.3, te=12.3-24325 a=0.3
8. NACA63-214 a=0.5
9. GA 35-214
10. NACA63-214 a=0.6
11. NACA63-314
12. GA 30-213
13. NACA63-214 a=0.8
14. NACA2213
15. NACA63-314 a=0.5
16. NACA63-214 a=0.2
17. NACA63-313 a=0.0
18. Rosner t=35.0 f=13.0, rN=1.3, te=15.1-19500 a=0.4
19. NACA63-313 a=0.2
20. NACA64-314 a=0.0
21. NACA64-314 a=0.2