Similarly shaped airfoils to NACA65-310 a=0.5
New! Bulk download of polars in Excel format: NACA65-310%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
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2. NACA64-310 a=0.5
3. GA 40-210
4. GA 40A210
5. NACA64-310 a=0.6
6. GA 37A210
7. NACA65-310 a=0.8
8. NACA65-310 a=0.2
9. GA 35A210
10. NACA65-410 a=0.0
11. NACA64A310
12. NACA63-310 a=0.5
13. DP1.87/9.07_DS
14. NACA63-310 a=0.6
15. NACA65-410
16. NACA63A310
17. GA 37-210
18. NACA66-310 a=0.5
19. NACA64-310 a=0.8
20. NACA65A310
21. SB98 VS5 tip