Similarly shaped airfoils to Rosner t=35.0 f=6.0, rN=0.3, te=7.1-17600 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D6.0%2C%20rN%3D0.3%2C%20te%3D7.1-17600%20a%3D0.4.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. D6213-S
3. Rosner t=30.0 f=6.0, rN=0.3, te=5.7-21700 a=0.3
4. Rosner t=45.0 f=6.0, rN=0.3, te=11.4-14400 a=0.6
5. RAF 25
6. D6515-S
7. Rosner t=45.0 f=6.0, rN=0.3, te=11.4-13000 a=0.6
8. GOE 598
9. MJP712
10. Rosner t=30.0 f=6.0, rN=0.3, te=5.7-24325 a=0.3
11. A6018-S
12. Rosner t=35.0 f=7.0, rN=0.4, te=8.3-17600 a=0.4
13. Rosner t=30.0 f=7.0, rN=0.4, te=6.7-21700 a=0.3
14. TsAGI B 6.0% thick
15. Rosner t=35.0 f=7.0, rN=0.4, te=8.3-19500 a=0.4
16. TsAGI B 6.5% thick
17. NACA M10 (NACA-TR-221)
18. BOEING VERTOL V13006-.7
19. RG 14A-1.4/7.0
20. MB7136
21. NACA M10