Similarly shaped airfoils to NACA65-209 a=0.2
New! Bulk download of polars in Excel format: NACA65-209%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. NACA65-209 a=0.5
3. NACA64-209 a=0.2
4. GIII BL126
5. NACA64-209 a=0.0
6. GIII BL288
7. GIII BL207
8. NACA65-209 a=0.6
9. GIII BL167
10. GIII BL145
11. NACA64-209 a=0.5
12. DU 86-084/18
13. GIII BL332
14. NACA63-209 a=0.2
15. NACA65-209
16. NACA63-209 a=0.0
17. NACA65-209 a=0.8
18. NACA64-209 a=0.6
19. NACA66-209 a=0.2
20. NACA64A209
21. NACA66-209 a=0.0