Similarly shaped airfoils to NACA64-210 a=0.5
New! Bulk download of polars in Excel format: NACA64-210%20a%3D0.5.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. NACA63-210 a=0.5
3. NACA63-210 a=0.6
4. NACA64-210 a=0.8
5. NACA64-210 a=0.2
6. NACA63-210 a=0.8
7. NACA65-210 a=0.5
8. NACA63-210 a=0.2
9. NACA65-210 a=0.6
10. NACA64-210 a=0.0
11. NACA63A210
12. NACA64-210
13. NACA63-210 a=0.0
14. NACA65-210 a=0.8
15. NACA65-210 a=0.2
16. NACA64A210
17. NACA63-210
18. SB96VS 9.75/1.25
19. NACA64-310 a=0.0
20. HQ 1.0/10
21. NACA63-310 a=0.0