Similarly shaped airfoils to NACA65-710 a=0.2
New! Bulk download of polars in Excel format: NACA65-710%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. NACA65-710 a=0.0
3. NACA63-710 a=0.2
4. NACA66-710 a=0.2
5. NACA64-710 a=0.0
6. NACA65-711 a=0.2
7. NACA65-709 a=0.2
8. NACA64-711 a=0.2
9. NACA66-709 a=0.2
10. NACA66-710 a=0.0
11. NACA63-710 a=0.0
12. NACA65-709 a=0.0
13. NACA63-711 a=0.2
14. NACA66-709 a=0.0
15. GOE 385
16. NACA64-709 a=0.2
17. GOE 167 (V.KARMAN PROP.2)
18. NACA65-610 a=0.2
19. NACA65-610 a=0.5
20. NACA65-711 a=0.0
21. GA 40A610