Similarly shaped airfoils to RC-12(B)3
New! Bulk download of polars in Excel format: rc12b3.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
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. NACA M6
3. TsAGI B 12.5% thick
4. ONERA OA212
5. NACA M12
6. TsAGI B 12.0% thick
7. TsAGI B 13.0% thick
8. GOE 676 (= M 12)
9. GOE 704
10. NACA67-412 a=0.0
11. ZAGI 12
12. NACA66-413 a=0.0
13. NACA66-412 a=0.0
14. EPPLER 231
15. Europa Dykins 12%
16. NACA67-412 a=0.2
17. NACA67-312 a=0.2
18. NACA66-413 a=0.2
19. NACA66-312 a=0.2
20. NACA66-412 a=0.2
21. NACA66-313 a=0.2