Similarly shaped airfoils to NACA65-314 a=0.2
New! Bulk download of polars in Excel format: NACA65-314%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. GA 40-214
3. GA 40A214
4. NACA65-414 a=0.0
5. NACA65-314 a=0.5
6. NACA64-314 a=0.2
7. GA 37A214
8. NACA64-314 a=0.0
9. NACA65-214 a=0.5
10. NACA65-315 a=0.2
11. GA 35A214
12. NACA65-313 a=0.2
13. NACA65-314 a=0.6
14. NACA65-214 a=0.6
15. NACA65-313 a=0.0
16. HSNLF(1)-0213
17. NACA64-414 a=0.0
18. NACA65-315 a=0.0
19. GA 37-214
20. NACA64-314 a=0.5
21. NACA65-314