Similarly shaped airfoils to NACA65(2)-215
New! Bulk download of polars in Excel format: NACA65%282%29-215.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
3. NACA65-215 a=0.6
4. NACA65-215 a=0.5
5. NACA64A215
6. NACA65-315
7. NACA63A215
8. NACA65-215 a=0.2
9. NACA64(2)-215
10. NACA64-215 a=0.8
11. NACA65A215
12. NACA65-215 a=0.0
13. NACA64-215
14. NACA65-214 a=0.8
15. NACA64-215 a=0.6
16. NACA65-216 a=0.8
17. NACA65-214
18. NACA64A214
19. NACA64-315
20. NACA65A214
21. NACA64-215 a=0.5