Similarly shaped airfoils to NACA65-314 a=0.8
New! Bulk download of polars in Excel format: NACA65-314%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. NACA65-314 a=0.6
3. NACA64A314
4. GA 40-214
5. GA 40A214
6. NACA65-314 a=0.5
7. NACA65-314
8. NACA63A314
9. NACA64-314 a=0.8
10. NACA65A314
11. GA 37A214
12. NACA64-414
13. NACA64-314 a=0.6
14. NACA65-315 a=0.8
15. NACA65-313 a=0.8
16. NACA65A313
17. GA 35A214
18. NACA64A313
19. NACA65-415
20. NACA65-413
21. NACA64-314 a=0.5