Similarly shaped airfoils to NACA63-719 a=0.8
New! Bulk download of polars in Excel format: NACA63-719%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. NACA63-720 a=0.8
3. NACA63-718 a=0.8
4. NACA64-718 a=0.8
5. NACA64-720 a=0.8
6. FX 66-S-196 V1
7. NACA63-719 a=0.6
8. FX S 02-196
9. NACA63-619 a=0.8
10. NACA64-719 a=0.6
11. NACA63A718
12. GOE 420
13. FX 66-S-196
14. NACA63A719
15. GA 35-619
16. HQ 3.5/18
17. NACA63-619 a=0.6
18. NACA64-619 a=0.8
19. EPPLER 1098
20. NACA63-718 a=0.6
21. NACA63-720 a=0.6