Similarly shaped airfoils to NACA65-615 a=0.5
New! Bulk download of polars in Excel format: NACA65-615%20a%3D0.5.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. AH 81-K-144/17
3. NACA64-615 a=0.5
4. FX 78-K-150/20
5. NACA65-616 a=0.5
6. NACA65-614 a=0.5
7. NACA64-615 a=0.6
8. FX 84-W-150
9. GA 40-615
10. GA 40A615
11. NACA65-616 a=0.6
12. NACA65-614 a=0.6
13. FX 78-K-140/20
14. NACA64-616 a=0.5
15. GA 37A615
16. FX 78-K-140 A/20
17. NACA64-616 a=0.6
18. NACA65-715 a=0.2
19. NACA63-615 a=0.5
20. AH 83-150 Q
21. DU 99-146