Similarly shaped airfoils to NACA65-215 a=0.6
New! Bulk download of polars in Excel format: NACA65-215%20a%3D0.6.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. NACA65-215 a=0.8
3. NACA65(2)-215
4. NACA65-215
5. NACA65-215 a=0.2
6. NACA65-315
7. NACA64A215
8. NACA65-315 a=0.0
9. NACA65-215 a=0.0
10. NACA63A215
11. NACA64-215 a=0.6
12. NACA64-215 a=0.5
13. NACA64-215 a=0.8
14. NACA65A215
15. NACA65-216 a=0.6
16. NACA65-214 a=0.6
17. NACA65-214 a=0.5
18. NACA65-315 a=0.2
19. NACA65-216 a=0.5
20. NACA64(2)-215
21. NACA65-216 a=0.8