Similarly shaped airfoils to Rosner t=45.0 f=8.0, rN=0.5, te=15.0-13000 a=0.6
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D8.0%2C%20rN%3D0.5%2C%20te%3D15.0-13000%20a%3D0.6.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. RC08-64C
3. RC-08(B)3
4. GIII BL145
5. GIII BL167
6. MH 23 8%
7. GIII BL207
8. SM085013
9. MH 54 Speed
10. MH 54
11. DU 86-084/18
12. opit ffd
13. GIII BL126
14. NACA66-209
15. NACA65-209
16. MH 34
17. NACA65A109
18. GIII BL288
19. Rosner t=45.0 f=9.0, rN=0.6, te=16.8-13000 a=0.6
20. Rosner t=45.0 f=7.0, rN=0.4, te=13.2-13000 a=0.6
21. Rosner t=45.0 f=9.0, rN=0.6, te=16.8-14400 a=0.6