Similarly shaped airfoils to Rosner t=30.0 f=18.0, rN=2.5, te=16.8-24325 a=0.3
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D18.0%2C%20rN%3D2.5%2C%20te%3D16.8-24325%20a%3D0.3.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. Rosner t=30.0 f=17.0, rN=2.2, te=15.9-24325 a=0.3
3. Rosner t=30.0 f=17.0, rN=2.2, te=15.9-21700 a=0.3
4. NACA63-318 a=0.5
5. GA 35-218
6. NACA63-318 a=0.6
7. NACA63-318 a=0.2
8. Joukowsky 18.00% thick 2.00% camber
9. NACA63-418 a=0.0
10. GA 35-217
11. NACA63-317 a=0.5
12. NACA63-318 a=0.8
13. NACA63-317 a=0.2
14. NACA63-318
15. NACA63-317 a=0.6
16. NACA63-318 a=0.0
17. GA 30-217
18. NACA63-418 a=0.2
19. NACA63-418
20. NACA2317
21. NACA63-417 a=0.0