Similarly shaped airfoils to NACA65-214 a=0.2
New! Bulk download of polars in Excel format: NACA65-214%20a%3D0.2.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
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=0.5
3. NACA65-214 a=0.6
4. NACA65-214
5. NACA64-214 a=0.2
6. NACA65-214 a=0.8
7. NACA65-314 a=0.0
8. HSNLF(1)-0213
9. NACA64-214 a=0.0
10. NACA64-214 a=0.5
11. NACA64A214
12. NACA65-215 a=0.2
13. NACA65-213 a=0.2
14. NACA65-213 a=0.0
15. NACA65-215 a=0.0
16. NACA65-114 a=0.5
17. NACA64-214 a=0.6
18. NACA65-114 a=0.6
19. NACA63A214
20. NACA65-215 a=0.5
21. NACA64-314 a=0.0