Similarly shaped airfoils to Rosner t=45.0 f=6.0, rN=0.3, te=11.4
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D6.0%2C%20rN%3D0.3%2C%20te%3D11.4.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
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.
2. NACA M1 (NACA-TR-221)
3. NACA M1
4. GOE 444
5. Rosner t=35.0 f=6.0, rN=0.3, te=7.1
6. EPPLER EA 8(-1)-006
7. NACA0006
8. SC(2)-0406
9. Rosner t=35.0 f=7.0, rN=0.4, te=8.3
10. Rosner t=45.0 f=7.0, rN=0.4, te=13.2
11. S1010 HPV airfoil
12. SC(2)-0606
13. Rosner t=30.0 f=6.0, rN=0.3, te=5.7
14. BOEING-VERTOL VR-9
15. HQ 0/7
16. SC(2)-0706
17. Rosner t=30.0 f=7.0, rN=0.4, te=6.7
18. GOE 443
19. ONERA OA206
20. RAF 30 MOD
21. HN-311S