Similarly shaped airfoils to Rosner t=30.0 f=17.0, rN=2.2, te=15.9
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D17.0%2C%20rN%3D2.2%2C%20te%3D15.9.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=30.0 f=16.0, rN=2.0, te=15.0
3. EPPLER 479
4. Joukowsky 17.00% thick 0.00% camber
5. Horten 16.00% thick 0.00% camber
6. GOE 410
7. GA 35-017
8. SU-26M
9. GA 35-016
10. Joukowsky 18.00% thick 0.00% camber
11. GA 30-016
12. NACA63-117 a=0.0
13. NACA63-117
14. Joukowsky 16.00% thick 0.00% camber
15. NACA0016
16. Horten 17.00% thick 0.00% camber
17. EPPLER 477
18. NACA63-117 a=0.2
19. EPPLER 476
20. Rosner t=35.0 f=16.0, rN=2.0, te=18.4
21. EPPLER 478