Similarly shaped airfoils to NACA65-720 a=0.8
New! Bulk download of polars in Excel format: NACA65-720%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. NACA65-719 a=0.8
3. NACA63A720
4. NACA64A719
5. NACA65-720 a=0.6
6. NACA64-720 a=0.8
7. NACA65A719
8. NACA63A719
9. NACA65A720
10. NACA65-620 a=0.8
11. GA 40-620
12. FX 75-193
13. NACA65-620 a=0.6
14. GA 40A620
15. NACA65-719 a=0.6
16. NACA65-619 a=0.8
17. NACA64A620
18. GA 37A620
19. NACA65-720 a=0.5
20. NACA64-720 a=0.6
21. NACA65-619 a=0.6