Similarly shaped airfoils to Rosner t=35.0 f=16.0, rN=2.0, te=18.4-17600 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D16.0%2C%20rN%3D2.0%2C%20te%3D18.4-17600%20a%3D0.4.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
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2. NACA63A216
3. P-51D ROOT (BL17.5)
4. NACA64-217 a=0.5
5. NACA64-217 a=0.6
6. NACA64A216
7. Rosner t=35.0 f=17.0, rN=2.2, te=19.4-17600 a=0.4
8. Rosner t=35.0 f=15.0, rN=1.7, te=17.3-17600 a=0.4
9. NACA64-216 a=0.5
10. NACA64-216 a=0.6
11. NACA63-217 a=0.5
12. Rosner t=35.0 f=17.0, rN=2.2, te=19.4-19500 a=0.4
13. NACA64-217 a=0.8
14. Rosner t=35.0 f=15.0, rN=1.7, te=17.3-19500 a=0.4
15. NACA63-217 a=0.6
16. NACA64-317 a=0.0
17. NACA64-317
18. NACA63-216 a=0.5
19. NACA64-216 a=0.8
20. AS5046 (16%)
21. NACA63-216 a=0.6