Similarly shaped airfoils to Rosner t=30.0 f=8.0, rN=0.5, te=7.6
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D8.0%2C%20rN%3D0.5%2C%20te%3D7.6.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. RAF 30 MOD
3. HQ 0/9
4. HN-470s
5. HN-311S
6. HN-30s
7. DA8000
8. NACA0008
9. HN-315S
10. FAD07
11. HN-153S
12. TP28 tip
13. Rosner t=35.0 f=8.0, rN=0.5, te=9.4
14. FX 77-080
15. HQ 0/7
16. HN-33S
17. MH 50
18. Rosner t=35.0 f=7.0, rN=0.4, te=8.3
19. Rosner t=30.0 f=9.0, rN=0.6, te=8.6
20. Rosner t=30.0 f=7.0, rN=0.4, te=6.7
21. RS004at