Similarly shaped airfoils to Rosner t=30.0 f=9.0, rN=0.6, te=8.6-24325 a=0.3
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D9.0%2C%20rN%3D0.6%2C%20te%3D8.6-24325%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. Rosner t=30.0 f=9.0, rN=0.6, te=8.6-21700 a=0.3
3. MH 43 8.5%
4. RS004a
5. NACA63-309 a=0.0
6. NACA63-309 a=0.2
7. MVE8.516
8. MH 46 9.1%
9. SM8516m
10. MH 62 9.3%
11. DD928416
12. RAINER_TEST_3-mod 8.8
13. MG08
14. NACA2309
15. RG 14
16. NACA64-309 a=0.0
17. JWL075 8.8/1.76
18. NACA64-309 a=0.2
19. MH 20 9.01%
20. HQ 1.5/9
21. NACA2209