Similarly shaped airfoils to NACA65-715 a=0.5
New! Bulk download of polars in Excel format: NACA65-715%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 40-615
3. GA 40A615
4. GA 37A615
5. FX 67-K-150/17
6. NACA64-715 a=0.5
7. NACA65-716 a=0.5
8. NACA65-714 a=0.5
9. GA 35A615
10. NACA64-715 a=0.6
11. NACA65-716 a=0.6
12. GA 37-615
13. GA 40-616
14. GA 40A616
15. NACA64-716 a=0.5
16. NACA65-714 a=0.6
17. GA 40A614
18. GA 40-614
19. GA 37A614
20. NACA64-716 a=0.6
21. AH 81-K-144/17