Similarly shaped airfoils to NACA65-310 a=0.8
New! Bulk download of polars in Excel format: NACA65-310%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. NACA65-410
3. NACA65-310 a=0.6
4. NACA63A310
5. NACA65A310
6. NACA64-310 a=0.8
7. NACA64-410
8. NACA65-310 a=0.5
9. NACA65-310
10. NACA64-310 a=0.6
11. GA 40-210
12. GA 40A210
13. SB98 VS5 tip
14. NACA63-310 a=0.8
15. GA 37A210
16. NACA66-310 a=0.8
17. NACA66A310
18. NACA64-310 a=0.5
19. NACA63-410
20. NACA65A309
21. NACA64-310