Similarly shaped airfoils to Rosner t=35.0 f=7.0, rN=0.4, te=8.3-17600 a=0.4
New! Bulk download of polars in Excel format: Rosner%20t%3D35.0%20f%3D7.0%2C%20rN%3D0.4%2C%20te%3D8.3-17600%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
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. RG 14A-1.4/7.0
3. MJP712
4. MH 33
5. MB7136
6. MB714
7. Rosner t=30.0 f=7.0, rN=0.4, te=6.7-21700 a=0.3
8. SIKORSKY SSC-A07
9. TsAGI B 7.0% thick
10. Rosner t=45.0 f=7.0, rN=0.4, te=13.2-14400 a=0.6
11. GOE 598
12. BOEING-VERTOL VR-8 WITH TAB
13. BOEING-VERTOL VR-8
14. RAF 25
15. Rosner t=45.0 f=7.0, rN=0.4, te=13.2-13000 a=0.6
16. Rosner t=35.0 f=8.0, rN=0.5, te=9.4-17600 a=0.4
17. Rosner t=35.0 f=6.0, rN=0.3, te=7.1-17600 a=0.4
18. TsAGI B 6.5% thick
19. A7018-S
20. TsAGI B 6,49%
21. D6515-S