Similarly shaped airfoils to NACA65-613 a=0.5
New! Bulk download of polars in Excel format: NACA65-613%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 80-129
3. NACA64-613 a=0.5
4. GA 40-613
5. GA 40A613
6. NACA64-613 a=0.6
7. AH 63-K-127/24
8. NACA65-614 a=0.5
9. NACA65-612 a=0.5
10. GA 37A613
11. FX 74-130 WP2 MOD
12. NACA64-614 a=0.5
13. NACA65-614 a=0.6
14. NACA63-613 a=0.5
15. GA 35A613
16. NACA65-612 a=0.6
17. FX 84-W-127
18. FX 74-130 WP2
19. NACA64-614 a=0.6
20. NACA66-613 a=0.5
21. NACA66-612 a=0.5