Similarly shaped airfoils to NACA64-615 a=0.5
New! Bulk download of polars in Excel format: NACA64-615%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. NACA64-615 a=0.6
3. NACA63-615 a=0.6
4. NACA65-615 a=0.5
5. NACA64-616 a=0.5
6. NACA64-614 a=0.5
7. NACA63-614 a=0.5
8. NACA63-616 a=0.5
9. NACA65-615 a=0.6
10. FX 84-W-150
11. NACA64-616 a=0.6
12. NACA64-614 a=0.6
13. AH 93-W-145
14. NACA65-614 a=0.5
15. NACA63-616 a=0.6
16. NACA63-614 a=0.6
17. FX 84-W-140
18. FX 79-W-151 A
19. GA 37-615
20. AH 81-K-144/17
21. NACA64-715 a=0.2