Similarly shaped airfoils to NACA63-515 a=0.8
New! Bulk download of polars in Excel format: NACA63-515%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. NACA64-515 a=0.8
3. NACA64-615
4. NACA63-515 a=0.6
5. EM J18 3015 DrW r0,8
6. NACA64-515 a=0.6
7. NACA63-516 a=0.8
8. NACA63-514 a=0.8
9. HQ 3.0/15
10. NACA63-616
11. NACA63-614
12. GA 35-415
13. NACA64-514 a=0.8
14. NACA64-516 a=0.8
15. EM J18 1 3015
16. NACA63-715
17. NACA63A515
18. HQ 3.0/14
19. NACA64-614
20. GA 37-415
21. NACA64-616