Similarly shaped airfoils to RC-12(N)1
New! Bulk download of polars in Excel format: rc12n1.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
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. NACA65-212 a=0.0
3. NACA64-212 a=0.2
4. NACA64-212 a=0.0
5. EPPLER 361
6. EPPLER 360
7. NACA65-312 a=0.0
8. NACA64-312 a=0.0
9. NACA65-212 a=0.5
10. ONERA NACA CAMBRE
11. TsAGI B 11.5% thick
12. NACA63-212 a=0.2
13. TsAGI B 11.0% thick
14. NACA64-212 a=0.5
15. NACA64-213 a=0.2
16. NACA63-212 a=0.0
17. NPL 9660
18. NPL 9615
19. NACA64-313 a=0.0
20. NACA65-212 a=0.6
21. ZAGI 12