Similarly shaped airfoils to NACA65-214 a=0.5
New! Bulk download of polars in Excel format: NACA65-214%20a%3D0.5.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=0.2
4. NACA65-214
5. NACA65-314 a=0.0
6. NACA65-214 a=0.0
7. NACA64A214
8. NACA65-314
9. NACA64-214 a=0.5
10. NACA64-214 a=0.6
11. NACA63A214
12. HSNLF(1)-0213
13. NACA65-314 a=0.2
14. NACA64-214 a=0.8
15. NACA65A214
16. NACA65-215 a=0.5
17. NACA65-213 a=0.5
18. NACA65-215 a=0.6
19. NACA64-214 a=0.2
20. NACA65-213 a=0.6
21. NACA64-314 a=0.0