Similarly shaped airfoils to NACA63-615 a=0.5
New! Bulk download of polars in Excel format: NACA63-615%20a%3D0.5.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. NACA63-615 a=0.6
3. NACA64-615 a=0.6
4. NACA63-616 a=0.5
5. NACA63-614 a=0.5
6. NACA64-614 a=0.5
7. NACA64-616 a=0.5
8. NACA63-616 a=0.6
9. AH 93-W-145
10. NACA63-614 a=0.6
11. NACA64-616 a=0.6
12. FX 84-W-150
13. NACA64-614 a=0.6
14. GA 35-615
15. NACA63-715 a=0.2
16. FX 79-W-151 A
17. GA 37-615
18. NACA65-615 a=0.5
19. FX 84-W-140
20. NACA64-715 a=0.2
21. NACA63-515 a=0.6