Similarly shaped airfoils to NACA65-516 a=0.2
New! Bulk download of polars in Excel format: NACA65-516%20a%3D0.2.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. NACA65-616 a=0.0
3. EPPLER 642
4. NACA64-516 a=0.2
5. NACA65-517 a=0.2
6. NACA65-515 a=0.2
7. NACA65-416 a=0.5
8. NACA64-616 a=0.0
9. RONCZ 1082T VOYAGER TIP OUTER AFT WING
10. NACA 747A415
11. NACA65-515 a=0.0
12. GA 40-316
13. NACA65-617 a=0.0
14. GA 40A316
15. NACA65-517 a=0.0
16. NACA64-516 a=0.0
17. NACA65-416 a=0.2
18. NACA65-615 a=0.0
19. NACA65-616 a=0.2
20. NACA64-517 a=0.2
21. NACA64-617 a=0.0