Similarly shaped airfoils to RC10-64C
New! Bulk download of polars in Excel format: rc1064c.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. GIII BL75
3. NACA66-210 a=0.0
4. GIII BL86
5. RC-SC2
6. NACA67-210 a=0.0
7. NACA66-210 a=0.2
8. GIII BL45
9. NACA67-210 a=0.2
10. NACA66-210
11. KC-135 BL200.76
12. NACA65A110
13. NACA66-110 a=0.5
14. NACA66-110 a=0.6
15. NACA67-210
16. NACA65-211 a=0.0
17. NACA65A111
18. NACA65A210
19. NACA65A211
20. NACA66-211 a=0.0
21. NACA0010-34 a=0.8 c(li)=0.2