Similarly shaped airfoils to Rosner t=45.0 f=9.0, rN=0.6, te=16.8
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D9.0%2C%20rN%3D0.6%2C%20te%3D16.8.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. MH 52
3. Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft
4. MH 53
5. RAE 104
6. NACA64A-010
7. GA 37A010
8. Rosner t=35.0 f=9.0, rN=0.6, te=10.6
9. NACA65-009
10. GA 40A010
11. NACA0010-34
12. RAE 103
13. Rosner t=45.0 f=10.0, rN=0.8, te=18.5
14. Rosner t=45.0 f=8.0, rN=0.5, te=15.0
15. GA 40-010
16. ONERA D, SHARP TRAILING EDGE
17. LWK 80-100
18. ONERA D, BLUNT TRAILING EDGE
19. NACA63A010
20. GA 35A010
21. NACA66-109 a=0.0