Similarly shaped airfoils to Rosner t=30.0 f=6.0, rN=0.3, te=5.7
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D6.0%2C%20rN%3D0.3%2C%20te%3D5.7.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. Rosner t=35.0 f=6.0, rN=0.3, te=7.1
3. BOEING-VERTOL VR-9
4. SC(2)-0406
5. GOE 444
6. S1010 HPV airfoil
7. EPPLER EA 8(-1)-006
8. SC(2)-0606
9. NACA M1 (NACA-TR-221)
10. NACA M1
11. GOE 445
12. Rosner t=30.0 f=7.0, rN=0.4, te=6.7
13. SC(2)-0706
14. GOE 443
15. HT13
16. HQ 0/7
17. TP29-7%
18. NM08
19. Rosner t=45.0 f=6.0, rN=0.3, te=11.4
20. Rosner t=35.0 f=7.0, rN=0.4, te=8.3
21. TP96-0.5%