Similarly shaped airfoils to NACA65-117 a=0.5
New! Bulk download of polars in Excel format: NACA65-117%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. NACA65-117 a=0.8
3. NACA65-117 a=0.2
4. NACA65-117
5. NACA65-117 a=0.0
6. NACA64A117
7. NACA65-217 a=0.0
8. NACA65-217
9. NACA63A117
10. NACA65-217 a=0.2
11. NACA65-118 a=0.5
12. NACA65-116 a=0.5
13. NACA65-118 a=0.6
14. NACA65-116 a=0.6
15. NACA65-118 a=0.8
16. NACA65-116 a=0.8
17. NACA65-116 a=0.2
18. NACA64-117 a=0.5
19. NACA65-118 a=0.2
20. NACA64-117 a=0.6
21. NACA65-116