Similarly shaped airfoils to NACA65-120
New! Bulk download of polars in Excel format: NACA65-120.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. NACA65-120 a=0.6
3. NACA65-120 a=0.5
4. NACA65-120 a=0.2
5. NACA65-120 a=0.0
6. NACA64A120
7. GA 40-020
8. GA 40A020
9. NACA65-119
10. NACA65-220
11. NACA65-220 a=0.0
12. NACA65-119 a=0.8
13. NACA65-119 a=0.6
14. NACA65-119 a=0.5
15. NACA65-119 a=0.2
16. NACA65-119 a=0.0
17. NACA63A120
18. NACA64A119
19. GA 37A020
20. NACA65-220 a=0.2
21. GA 40-019