Similarly shaped airfoils to NACA65-315 a=0.5
New! Bulk download of polars in Excel format: NACA65-315%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
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2. GA 40-215
3. GA 40A215
4. GA 37A215
5. NACA65-315 a=0.8
6. NACA65-415 a=0.0
7. NACA65-315 a=0.2
8. NACA65-415
9. NACA64-315 a=0.5
10. GA 35A215
11. NACA64-315 a=0.6
12. NACA65-415 a=0.2
13. NACA64A315
14. NACA65-316 a=0.5
15. NACA65-314 a=0.5
16. GA 37-215
17. NACA65-316 a=0.6
18. NACA65-314 a=0.6
19. NACA65-315
20. GA 40-216
21. NACA63A315