Similarly shaped airfoils to NACA64A717
New! Bulk download of polars in Excel format: NACA64A717.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. NACA65-717 a=0.8
3. NACA65A717
4. NACA64A718
5. NACA64A716
6. NACA63A716
7. NACA65-718 a=0.8
8. NACA63A718
9. NACA64-717 a=0.8
10. NACA65A716
11. NACA64-718 a=0.8
12. NACA64A617
13. NACA65-617 a=0.8
14. Dees Okay230
15. NACA65-716 a=0.8
16. NACA63A617
17. FX 73-170
18. GA 37A617
19. NACA65-717 a=0.6
20. NACA65A617
21. EPPLER 655