Similarly shaped airfoils to Rosner t=30.0 f=13.0, rN=1.3, te=12.3
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D13.0%2C%20rN%3D1.3%2C%20te%3D12.3.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. GA 35-013
3. Horten 12.00% thick 0.00% camber
4. EPPLER EA 6(-1)-012
5. RAF 30
6. FX 79-L-120
7. EPPLER 171
8. Horten 13.00% thick 0.00% camber
9. GA 30-012
10. Rosner t=30.0 f=14.0, rN=1.5, te=13.2
11. Rosner t=30.0 f=12.0, rN=1.1, te=11.3
12. EPPLER 168
13. FX 76-120
14. Joukowsky 13.00% thick 0.00% camber
15. NACA0012
16. GA 37-013
17. FX LIII-142 K 25
18. GA 30A012
19. FX 71-120
20. NACA0013
21. NACA63-012