Similarly shaped airfoils to NACA64A214
New! Bulk download of polars in Excel format: NACA64A214.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. NACA65-214 a=0.8
3. NACA65-214 a=0.6
4. NACA65-214
5. NACA65-214 a=0.5
6. NACA65A214
7. NACA64-214 a=0.8
8. NACA65-314
9. NACA64-214 a=0.6
10. NACA65-214 a=0.2
11. NACA64-214
12. NACA64A215
13. NACA64A213
14. NACA64-214 a=0.5
15. NACA63A213
16. NACA65A213
17. NACA65-215 a=0.8
18. NACA65-214 a=0.0
19. NACA65(2)-215
20. NACA64-215 a=0.8
21. NACA63A215