Similarly shaped airfoils to Rosner t=35.0 f=9.0, rN=0.6, te=10.6-17600 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D9.0%2C%20rN%3D0.6%2C%20te%3D10.6-17600%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
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2. NACA63A209
3. NACA64-209 a=0.5
4. DU 86-084/18
5. NACA64-209 a=0.2
6. NACA65-209 a=0.5
7. MH 34
8. NACA65-209 a=0.2
9. NACA64A209
10. NACA64-209 a=0.6
11. GIII BL332
12. NACA63-209 a=0.5
13. NACA65-209 a=0.6
14. NACA63-209 a=0.2
15. HQ 1.0/9
16. SM085013
17. SIKORSKY SSC-A09
18. GIII BL288
19. NACA64-209 a=0.0
20. NACA65-209 a=0.0
21. RG-12