Similarly shaped airfoils to NACA65-616 a=0.6
New! Bulk download of polars in Excel format: NACA65-616%20a%3D0.6.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. NACA64-616 a=0.6
3. NACA65-617 a=0.6
4. NACA65-615 a=0.6
5. NACA65-616 a=0.8
6. NACA65-615 a=0.5
7. NACA64-616 a=0.5
8. NACA65-617 a=0.5
9. GA 40-616
10. GA 40A616
11. AH 83-159
12. NACA64-617 a=0.6
13. AH 94-156
14. NACA64A616
15. FX 84-W-150
16. FX 78-K-150/20
17. GA 37A616
18. NACA65-716
19. AH 93-156
20. NACA65-516 a=0.6
21. NACA64-617 a=0.5