Similarly shaped airfoils to NACA65-415 a=0.5
New! Bulk download of polars in Excel format: NACA65-415%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 40-315
3. GA 40A315
4. GA 37A315
5. GA 35A315
6. NACA64-415 a=0.5
7. NACA65(2)-415 a=0.5
8. NACA65-515 a=0.0
9. NACA64-415 a=0.6
10. NACA65-415 a=0.8
11. NACA65-416 a=0.5
12. NACA65-414 a=0.5
13. GA 37-315
14. MB253515 15.0% smoothed
15. NACA65-515 a=0.2
16. NACA65-415 a=0.2
17. NACA65-416 a=0.6
18. AH 79-K-143/18
19. GA 40-316
20. NACA65-414 a=0.6
21. FX 79-K-144/17