Similarly shaped airfoils to Rosner t=35.0 f=9.0, rN=0.6, te=10.6
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D9.0%2C%20rN%3D0.6%2C%20te%3D10.6.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. NACA0009
3. NACA64-009
4. NACA65-009
5. EH 0.0/9.0
6. Horten 9.00% thick 0.00% camber
7. NACA63-009
8. EPPLER EA 6(-1)-009
9. HN-316S
10. GA 37-010
11. RAE 102
12. GA 35A010
13. GA 37A010
14. Rosner t=30.0 f=9.0, rN=0.6, te=8.6
15. RAF 27
16. NACA M2 (NACA-TR-221)
17. RAE 101
18. NACA63A010
19. GA 35-010
20. HN-312S
21. TP36-9.5%