Similarly shaped airfoils to Rosner t=45.0 f=8.0, rN=0.5, te=15.0
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D8.0%2C%20rN%3D0.5%2C%20te%3D15.0.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. LWK 80-080
3. NACA M2
4. MH 50
5. NACA M2 (NACA-TR-221)
6. Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft
7. Rosner t=35.0 f=8.0, rN=0.5, te=9.4
8. NACA66-009
9. NACA65-009
10. Rosner t=45.0 f=9.0, rN=0.6, te=16.8
11. Rosner t=45.0 f=7.0, rN=0.4, te=13.2
12. Rosner t=35.0 f=9.0, rN=0.6, te=10.6
13. MH 52
14. NACA64-009
15. NACA0008
16. HN-470s
17. HQ 0/9
18. MH 54
19. MH 54 Speed
20. HN-153S
21. HN-30s