Similarly shaped airfoils to Rosner t=30.0 f=7.0, rN=0.4, te=6.7
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D7.0%2C%20rN%3D0.4%2C%20te%3D6.7.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. Rosner t=35.0 f=7.0, rN=0.4, te=8.3
3. GOE 445
4. EPPLER EA 8(-1)-006
5. NACA M1
6. NACA M1 (NACA-TR-221)
7. S1010 HPV airfoil
8. HN-968S
9. RAF 30 MOD
10. NACA0006
11. Rosner t=35.0 f=6.0, rN=0.3, te=7.1
12. Rosner t=30.0 f=8.0, rN=0.5, te=7.6
13. TP29-7%
14. SC(2)-0406
15. Rosner t=30.0 f=6.0, rN=0.3, te=5.7
16. HN-311S
17. FAD07
18. SC(2)-0606
19. BOEING-VERTOL VR-9
20. NM08
21. SC(2)-0706