Similarly shaped airfoils to Rosner t=35.0 f=6.0, rN=0.3, te=7.1
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D6.0%2C%20rN%3D0.3%2C%20te%3D7.1.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. GOE 444
3. EPPLER EA 8(-1)-006
4. GOE 445
5. NACA M1 (NACA-TR-221)
6. NACA M1
7. Rosner t=30.0 f=6.0, rN=0.3, te=5.7
8. SC(2)-0406
9. Rosner t=45.0 f=6.0, rN=0.3, te=11.4
10. S1010 HPV airfoil
11. BOEING-VERTOL VR-9
12. SC(2)-0606
13. Rosner t=30.0 f=7.0, rN=0.4, te=6.7
14. HQ 0/7
15. SC(2)-0706
16. Rosner t=35.0 f=7.0, rN=0.4, te=8.3
17. GOE 443
18. TP29-7%
19. Rosner t=45.0 f=7.0, rN=0.4, te=13.2
20. HT13
21. ONERA OA206