Similarly shaped airfoils to NACA64-209 a=0.8
New! Bulk download of polars in Excel format: NACA64-209%20a%3D0.8.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. NACA64-209 a=0.6
3. NACA63-209 a=0.6
4. NACA63A209
5. NACA64-209 a=0.5
6. NACA64-209
7. NACA65-209 a=0.8
8. NACA64A209
9. NACA63-209 a=0.5
10. NACA63-209
11. NACA65-209 a=0.6
12. NACA64-309
13. HQ 1.0/9
14. NACA63-309
15. NACA65-209 a=0.5
16. NACA65-209
17. NACA64-209 a=0.2
18. HQ 1.5/9 B
19. HQ 1.5/9
20. PROPFAN CRUISE MISSILE WING
21. HQ 1.5/8.5