Similarly shaped airfoils to Rosner t=45.0 f=10.0, rN=0.8, te=18.5


New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D10.0%2C%20rN%3D0.8%2C%20te%3D18.5.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
1. NACA0010-64
2. RAE 104
3. NACA0010-34
4. LWK 80-100
5. SC(2)-0010
6. ONERA D, SHARP TRAILING EDGE
7. ONERA D, BLUNT TRAILING EDGE
8. RAE 103
9. MH 53
10. NACA64A-010
11. GA 37A011
12. Rosner t=45.0 f=11.0, rN=0.9, te=20.2
13. Rosner t=45.0 f=9.0, rN=0.6, te=16.8
14. GA 40A011
15. GA 40-011
16. N-12
17. GA 37A010
18. Rosner t=35.0 f=10.0, rN=0.8, te=11.7
19. NACA0010-65
20. NACA63A010
21. NACA63A011