Similarly shaped airfoils to Rosner t=45.0 f=7.0, rN=0.4, te=13.2
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D7.0%2C%20rN%3D0.4%2C%20te%3D13.2.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. NACA0008-34
3. LWK 80-080
4. Rosner t=45.0 f=8.0, rN=0.5, te=15.0
5. Rosner t=45.0 f=6.0, rN=0.3, te=11.4
6. NACA M2
7. GOE 445
8. RAF 30 MOD
9. Rosner t=35.0 f=8.0, rN=0.5, te=9.4
10. MH 50
11. NACA M1
12. NACA M1 (NACA-TR-221)
13. HQ 0/7
14. EPPLER EA 8(-1)-006
15. HN-311S
16. NACA M2 (NACA-TR-221)
17. NACA0008
18. HQ 0/9
19. HN-470s
20. HN-968S
21. Rosner t=30.0 f=7.0, rN=0.4, te=6.7