Similarly shaped airfoils to Rosner t=45.0 f=6.0, rN=0.3, te=11.4-14400 a=0.6
New! Bulk download of polars in Excel format: Rosner%20t%3D45.0%20f%3D6.0%2C%20rN%3D0.3%2C%20te%3D11.4-14400%20a%3D0.6.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. Rosner t=35.0 f=6.0, rN=0.3, te=7.1-17600 a=0.4
3. GOE 598
4. RAF 25
5. Rosner t=35.0 f=6.0, rN=0.3, te=7.1-19500 a=0.4
6. TsAGI B 6.0% thick
7. Rosner t=45.0 f=7.0, rN=0.4, te=13.2-14400 a=0.6
8. Rosner t=45.0 f=7.0, rN=0.4, te=13.2-13000 a=0.6
9. TsAGI B 6,49%
10. TsAGI B 6.5% thick
11. Rosner t=35.0 f=7.0, rN=0.4, te=8.3-17600 a=0.4
12. Rosner t=35.0 f=7.0, rN=0.4, te=8.3-19500 a=0.4
13. BOEING VERTOL V13006-.7
14. D6213-S
15. SIKORSKY SSC-A07
16. ONERA OA206
17. opit ffd
18. MJP712
19. TsAGI B 7.0% thick
20. RG 14A-1.4/7.0
21. MH 33