Similarly shaped airfoils to NACA65-415 a=0.6
New! Bulk download of polars in Excel format: NACA65-415%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. GA 40-315
3. GA 40A315
4. NACA65-415 a=0.8
5. GA 37A315
6. NACA65-515
7. NACA65(2)-415 a=0.5
8. NACA64-415 a=0.6
9. NACA64A415
10. GA 35A315
11. NACA64-415 a=0.5
12. NACA65-416 a=0.6
13. NACA65-414 a=0.6
14. GA 37-315
15. NACA65-414 a=0.5
16. NACA65(2)-415
17. NACA65-416 a=0.5
18. FX 79-K-144/17
19. NACA63A415
20. GA 40-316
21. GA 40A316