Similarly shaped airfoils to NACA65-315 a=0.2
New! Bulk download of polars in Excel format: NACA65-315%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 40-215
3. GA 40A215
4. NACA65-415 a=0.0
5. NACA65-315 a=0.5
6. NACA64-315 a=0.2
7. GA 37A215
8. NACA65-215 a=0.5
9. NACA65-316 a=0.2
10. NACA65-314 a=0.2
11. NACA64-315 a=0.0
12. NACA65-215 a=0.6
13. NACA65-315 a=0.6
14. NACA65-314 a=0.0
15. GA 35A215
16. NACA65-316 a=0.0
17. NACA64-415 a=0.0
18. NACA65-315
19. GA 37-215
20. NACA65-215 a=0.2
21. NACA64-315 a=0.5