Similarly shaped airfoils to NACA65-716 a=0.8
New! Bulk download of polars in Excel format: NACA65-716%20a%3D0.8.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. NACA63A716
3. NACA64-716 a=0.8
4. NACA65A716
5. NACA65-717 a=0.8
6. NACA65-715 a=0.8
7. NACA64A715
8. NACA65A715
9. NACA63A715
10. NACA65-716 a=0.6
11. NACA64-717 a=0.8
12. EPPLER 657
13. FX 73-170
14. EPPLER 435
15. NACA64A717
16. EPPLER 431
17. NACA65-616 a=0.8
18. EPPLER 662
19. NACA63-716 a=0.8
20. FX 73-K-170/22
21. NACA66A715