Similarly shaped airfoils to NACA65-209 a=0.0
New! Bulk download of polars in Excel format: NACA65-209%20a%3D0.0.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. GIII BL126
3. NACA64-209 a=0.0
4. NACA64-209 a=0.2
5. GIII BL207
6. GIII BL288
7. NACA65-209 a=0.5
8. GIII BL167
9. DU 86-084/18
10. NACA65-209
11. GIII BL145
12. NACA63-209 a=0.0
13. NACA63-209 a=0.2
14. NACA65-209 a=0.6
15. GIII BL332
16. NACA66-209 a=0.0
17. NACA64-209 a=0.5
18. NACA66-209 a=0.2
19. NACA64-209
20. NACA65-209 a=0.8
21. TsAGI B 8.5% thick