Similarly shaped airfoils to NACA63A711
New! Bulk download of polars in Excel format: NACA63A711.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. NACA64-711 a=0.8
3. NACA65-711 a=0.8
4. NACA63-711 a=0.8
5. NACA65A711
6. NACA64-712 a=0.8
7. EPPLER 214
8. NACA63A712
9. NACA63A710
10. NACA64A712
11. NACA63-712 a=0.8
12. S4022
13. NACA64A710
14. NACA65-712 a=0.8
15. NACA65A710
16. FX 83-W-108
17. GOE 547
18. EPPLER 66
19. NACA65-611 a=0.8
20. NACA65-710 a=0.8
21. NACA64-611 a=0.8