Similarly shaped airfoils to NACA63-315
New! Bulk download of polars in Excel format: NACA63-315.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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. NACA63-215 a=0.8
3. NACA63-215 a=0.6
4. NACA63-315 a=0.8
5. NACA64-215 a=0.8
6. NACA64(2)-215
7. NACA64-215 a=0.6
8. NACA63-215 a=0.5
9. NACA64-315 a=0.8
10. GA 35-215
11. NACA64-215 a=0.5
12. GA 37-215
13. NACA63-316
14. NACA63-314
15. AS5045 (15%)
16. NACA63-315 a=0.6
17. NACA63-415
18. NACA64-314
19. NACA63-315 a=0.5
20. NACA63-215
21. NACA64-316