Similarly shaped airfoils to NACA63-215 a=0.8
New! Bulk download of polars in Excel format: NACA63-215%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. NACA64-215 a=0.8
3. NACA63-215
4. NACA63-215 a=0.5
5. NACA64(2)-215
6. NACA64-215 a=0.6
7. NACA63-315
8. NACA64-215 a=0.5
9. NACA64-215
10. NACA64-315
11. NACA63-215 a=0.2
12. AS5045 (15%)
13. NACA64-215 a=0.2
14. NACA63-216 a=0.8
15. NACA63-214 a=0.8
16. NACA63-215 a=0.0
17. NACA63-216 a=0.6
18. NACA63-214 a=0.6
19. NACA64-214 a=0.8
20. NACA64-216 a=0.8
21. NACA63A215