Similarly shaped airfoils to NACA65-618
New! Bulk download of polars in Excel format: NACA65-618.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (14) | 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. FX S 03-182
3. NACA64A518
4. NACA65-619
5. NACA65-617
6. NACA63A518
7. NACA65-517 a=0.8
8. NACA65-519 a=0.8
9. NACA65-518 a=0.6
10. NACA65-518
11. NACA65-718
12. NACA64-618
13. NACA64A517
14. GA 40-418
15. GA 40A418
16. NACA64-518 a=0.8
17. NACA65A518
18. FX 05-188
19. NACA65A517
20. NACA65-418 a=0.8
21. DU 80-176 V1 alt