Similarly shaped airfoils to NACA65-620 a=0.8
New! Bulk download of polars in Excel format: NACA65-620%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. NACA64A620
3. NACA65-619 a=0.8
4. NACA65-620 a=0.6
5. NACA63A620
6. NACA65-719
7. NACA64A619
8. NACA64-620 a=0.8
9. NACA63A619
10. NACA65A619
11. NACA65-520 a=0.8
12. NACA65A620
13. NACA65-720 a=0.8
14. GA 40-420
15. NACA64-720
16. NACA65-520 a=0.6
17. GA 40A420
18. NACA65-619 a=0.6
19. NACA64A720
20. FX 75-193
21. NACA65-620 a=0.5