Similarly shaped airfoils to Rosner t=30.0 f=16.0, rN=2.0, te=15.0-21700 a=0.3
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D16.0%2C%20rN%3D2.0%2C%20te%3D15.0-21700%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=17.0, rN=2.2, te=15.9-21700 a=0.3
3. Rosner t=30.0 f=15.0, rN=1.7, te=14.1-21700 a=0.3
4. Rosner t=30.0 f=17.0, rN=2.2, te=15.9-24325 a=0.3
5. Rosner t=30.0 f=15.0, rN=1.7, te=14.1-24325 a=0.3
6. NACA63-316 a=0.2
7. NACA63-316 a=0.0
8. NACA63-215 MOD B
9. GOE 738
10. GA 35-216
11. NACA63-216 a=0.5
12. NACA63-216 a=0.6
13. NACA63-316
14. MH 104 15.28%
15. NACA63-316 a=0.5
16. NACA2315
17. NACA63-315 a=0.2
18. NACA63-216 a=0.8
19. NACA63-315 a=0.0
20. NACA63-316 a=0.6
21. GA 30-215