Similarly shaped airfoils to NACA65-518 a=0.5
New! Bulk download of polars in Excel format: NACA65-518%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. GA 40-418
3. GA 40A418
4. GA 37A418
5. NACA65-519 a=0.5
6. NACA65-517 a=0.5
7. RONCZ 1080 VOYAGER INNER AFT WING
8. NACA65-519 a=0.6
9. NACA65-517 a=0.6
10. NACA64-518 a=0.5
11. NACA65-618 a=0.2
12. GA 35A418
13. GA 40-417
14. GA 40A417
15. RONCZ 1082 VOYAGER ROOT OUTER AFT WING
16. GA 37-418
17. NACA64-518 a=0.6
18. GA 40-419
19. NACA65-518 a=0.8
20. NACA65-618 a=0.0
21. GA 37A417