Similarly shaped airfoils to Rosner t=30.0 f=7.0, rN=0.4, te=6.7-24325 a=0.3
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D7.0%2C%20rN%3D0.4%2C%20te%3D6.7-24325%20a%3D0.3.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. MH 22 7.2%
3. A7018-S
4. S6063 7.05%
5. D7017-S
6. D6515-S
7. FAD06
8. MB714
9. UplinkDLG
10. NM12
11. RG 14A-1.4/7.0
12. DA7017
13. HN-1070
14. NACA M10
15. NACA25007
16. Rosner t=35.0 f=7.0, rN=0.4, te=8.3-19500 a=0.4
17. NM28
18. NACA M10 (NACA-TR-221)
19. AG45ct -02f
20. D7517-S
21. MG06