Similarly shaped airfoils to NACA64-715 a=0.2
New! Bulk download of polars in Excel format: NACA64-715%20a%3D0.2.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. NACA64-715 a=0.0
3. NACA63-715 a=0.0
4. NACA65-715 a=0.2
5. NACA64-716 a=0.2
6. NACA64-714 a=0.2
7. NACA63-714 a=0.2
8. NACA63-716 a=0.2
9. NACA65-715 a=0.0
10. AH 83-150 Q
11. NACA65-714 a=0.2
12. NACA64-714 a=0.0
13. NACA64-615 a=0.2
14. NACA63-714 a=0.0
15. NACA65-714 a=0.0
16. NACA63-615 a=0.2
17. NACA64-615 a=0.5
18. DEFIANT CANARD BL110
19. NACA64-716 a=0.0
20. NACA63-615 a=0.5
21. NACA63-716 a=0.0