Similarly shaped airfoils to NACA65-214
New! Bulk download of polars in Excel format: NACA65-214.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA65-214 a=0.6
3. NACA64A214
4. NACA65-214 a=0.5
5. NACA65-214 a=0.0
6. NACA65-214 a=0.2
7. NACA64-214
8. NACA65-114 a=0.6
9. NACA65-114 a=0.8
10. NACA63A214
11. NACA65(215)-114
12. NACA65-114 a=0.5
13. NACA64-214 a=0.8
14. NACA65A214
15. NACA65-215
16. NACA65-213
17. NACA64A114
18. NACA64-214 a=0.6
19. NACA65(2)-215
20. NACA65-114
21. NACA64-214 a=0.5