Similarly shaped airfoils to Rosner t=30.0 f=10.0, rN=0.8, te=9.5-24325 a=0.3


New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D10.0%2C%20rN%3D0.8%2C%20te%3D9.5-24325%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.

1. Rosner t=30.0 f=10.0, rN=0.8, te=9.5-21700 a=0.3
2. HM56
3. HM55
4. MH 44 9.66%
5. GA 35-210
6. RS001
7. NACA63-310 a=0.2
8. NM20 root
9. NACA63-310 a=0.0
10. MH 60 10.08%
11. HM10011
12. Ritz 2-30-10
13. TL55
14. TP-CIEL-S
15. MH 45 9.85%
16. GA 37-210
17. RG 14 9.5%
18. AZcombat1
19. NACA2310
20. HQ 1.5/10
21. TP210-10%