Similarly shaped airfoils to NACA64-615 a=0.8
New! Bulk download of polars in Excel format: NACA64-615%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. NACA64-715
3. NACA63-715
4. NACA63A615
5. NACA65-615 a=0.8
6. NACA63A614
7. NACA64A615
8. NACA64-616 a=0.8
9. NACA63(2)-615
10. NACA64-614 a=0.8
11. NACA65-715
12. NACA64-615 a=0.6
13. NACA63-614 a=0.8
14. FX 75-141
15. NACA63-616 a=0.8
16. NACA64A614
17. NACA64-714
18. NACA63-615 a=0.6
19. NACA64-716
20. NACA65-614 a=0.8
21. NACA63-714