Similarly shaped airfoils to NACA65-214 a=0.8
New! Bulk download of polars in Excel format: NACA65-214%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
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
4. NACA64A214
5. NACA65-314
6. NACA63A214
7. NACA64-214 a=0.8
8. NACA65A214
9. NACA65-214 a=0.2
10. NACA64-214 a=0.6
11. NACA65-214 a=0.0
12. NACA64-214 a=0.5
13. NACA64-214
14. NACA65-215 a=0.8
15. NACA65-213 a=0.8
16. NACA64-314
17. NACA65A213
18. NACA65(2)-215
19. NACA64A213
20. NACA65-215 a=0.6
21. NACA65-213 a=0.6