Similarly shaped airfoils to RC12-64C
New! Bulk download of polars in Excel format: rc1264c.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. AMSOIL2 RUTAN WING
3. LOCKHEED C-141 BL113.6
4. MH 17
5. NACA65A213
6. NACA66-212 a=0.0
7. NACA65A113
8. NACA66-212 a=0.2
9. NACA67-212 a=0.0
10. NACA67-212 a=0.2
11. LOCKHEED C-5A BL488.2
12. NACA65A212
13. NACA66-212
14. NACA66-213 a=0.0
15. NACA65A112
16. NACA66-213 a=0.2
17. NACA64A213
18. NACA67-212
19. LOCKHEED C-141 BL0
20. NACA66(1)-212
21. NACA66-213