Similarly shaped airfoils to NACA64-313
New! Bulk download of polars in Excel format: NACA64-313.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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. NACA64-213 a=0.8
3. NACA64-213 a=0.6
4. NACA63-213 a=0.8
5. NACA64-313 a=0.8
6. NACA65-313
7. NACA63-213 a=0.6
8. GA 37-213
9. NACA63-313 a=0.8
10. NACA64-213 a=0.5
11. NACA63-213 a=0.5
12. GA 35-213
13. HQ 1.5/12
14. NACA63A313
15. NACA65-213 a=0.8
16. NACA63A213
17. NACA64-314
18. NACA64-312
19. NACA65-213 a=0.6
20. NACA64-313 a=0.6
21. GA 35A213