Similarly shaped airfoils to NACA65A613
New! Bulk download of polars in Excel format: NACA65A613.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. NACA66A613
3. NACA66-613 a=0.8
4. NACA65-613 a=0.8
5. NACA66-713
6. NACA65-713
7. NACA63A613
8. AH 88-K-130/20
9. FX 74-130 WP1
10. NACA65A614
11. NACA65A612
12. NACA65-614 a=0.8
13. NACA64A614
14. NACA66A612
15. NACA66-612 a=0.8
16. NACA65-714
17. FX 74-130 WP2 MOD
18. NACA66-712
19. FX 74-130 WP2
20. NACA63A614
21. NACA66-613 a=0.6