Similarly shaped airfoils to NACA63-210 a=0.8
New! Bulk download of polars in Excel format: NACA63-210%20a%3D0.8.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=0.6
3. NACA64-210 a=0.6
4. NACA63-210 a=0.5
5. NACA63-210
6. NACA64-210 a=0.5
7. NACA64-210
8. HQ 1.0/10
9. NACA63-310
10. NACA63A210
11. NACA64-310
12. TP-CIEL-S
13. SB96VS 9.75/1.25
14. NACA64A210
15. NACA63-210 a=0.2
16. HQ 1.5/10
17. NACA65-210 a=0.8
18. NACA64-210 a=0.2
19. RG-12
20. NACA65-210 a=0.6
21. NACA63-210 a=0.0