Similarly shaped airfoils to Rosner t=35.0 f=8.0, rN=0.5, te=9.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D8.0%2C%20rN%3D0.5%2C%20te%3D9.4.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. HQ 0/9
3. HN-470s
4. LWK 80-080
5. NACA M2
6. NACA0008
7. NACA M2 (NACA-TR-221)
8. HN-30s
9. HN-153S
10. RAF 30 MOD
11. HN-315S
12. HN-311S
13. Rosner t=30.0 f=8.0, rN=0.5, te=7.6
14. FX 77-080
15. NACA64-009
16. DA8000
17. NACA63-009
18. HN-968S
19. HN-33S
20. Rosner t=45.0 f=8.0, rN=0.5, te=15.0
21. NACA0008-34