Similarly shaped airfoils to NACA63-710 a=0.8
New! Bulk download of polars in Excel format: NACA63-710%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. NACA63A710
3. NACA64A710
4. NACA65-710 a=0.8
5. NACA63A709
6. NACA63-711 a=0.8
7. NACA63-709 a=0.8
8. NACA64-709 a=0.8
9. NACA64-711 a=0.8
10. S4062-095-87
11. NACA5510
12. NACA64A709
13. NACA65-709 a=0.8
14. NACA5509
15. NACA63-710 a=0.6
16. GOE 392
17. PSU 94-097 (AIAA 2001-2478)
18. NACA64-710 a=0.6
19. EPPLER 66
20. FX 63-100
21. MH 116 9.84%