Similarly shaped airfoils to NACA64A615
New! Bulk download of polars in Excel format: NACA64A615.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. NACA65-615 a=0.8
3. NACA65-715
4. NACA65A615
5. NACA64-615 a=0.8
6. GOE 493
7. NACA64A616
8. NACA64A614
9. NACA63A614
10. NACA64-715
11. NACA65-616 a=0.8
12. NACA65A614
13. NACA63A616
14. NACA64-616 a=0.8
15. NACA65-716
16. NACA64-716
17. NACA65-615 a=0.6
18. NACA65-614 a=0.8
19. NACA65-515 a=0.8
20. FX 60-160
21. NACA63-615 a=0.8