Similarly shaped airfoils to Rosner t=30.0 f=11.0, rN=0.9, te=10.4-21700 a=0.3
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D11.0%2C%20rN%3D0.9%2C%20te%3D10.4-21700%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. HM50
3. NACA63-311 a=0.0
4. TPR-95-96-95
5. NACA63-211 a=0.5
6. NACA63-211 a=0.6
7. NACA63-311 a=0.2
8. GA 35-211
9. JWL081 11/1.3
10. HM10011
11. HQ 1.5/11
12. Rosner t=30.0 f=12.0, rN=1.1, te=11.3-21700 a=0.3
13. Rosner t=30.0 f=10.0, rN=0.8, te=9.5-21700 a=0.3
14. NACA64-311 a=0.0
15. NACA63-211 a=0.2
16. RG 14 10%
17. NACA64-211 a=0.5
18. NACA63-311
19. Rosner t=30.0 f=12.0, rN=1.1, te=11.3-24325 a=0.3
20. NACA63-211 a=0.8
21. MH 61 10.26%