Similarly shaped airfoils to NACA65-418 a=0.8
New! Bulk download of polars in Excel format: NACA65-418%20a%3D0.8.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
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2. NACA65-418 a=0.6
3. NACA64A418
4. GA 40-318
5. GA 40A318
6. NACA65-418
7. NACA63A418
8. NACA65-418 a=0.5
9. NACA65-419 a=0.8
10. NACA65-417 a=0.8
11. NACA65-519
12. NACA65-517
13. NACA64A417
14. NACA64-418 a=0.8
15. NACA64-518
16. NACA65A418
17. GA 37A318
18. NACA65A417
19. NACA65-417 a=0.6
20. NACA65-419 a=0.6
21. LS(1)-0417 (GA(W)-1)