Similarly shaped airfoils to NACA 747A315
New! Bulk download of polars in Excel format: NACA747A315.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (8) | 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. NACA65-415 a=0.0
3. NACA65-515 a=0.0
4. TsAGI B 14.5% thick
5. NACA64-415 a=0.2
6. NACA65-416 a=0.2
7. TsAGI B 14.0% thick
8. NACA64-415 a=0.0
9. NACA 747A415
10. NACA65-416 a=0.0
11. NACA64-515 a=0.0
12. NACA 5-H-15
13. NACA64-416 a=0.2
14. NACA64-516 a=0.0
15. TsAGI B 15.0% thick
16. NACA65-516 a=0.0
17. NACA64-416 a=0.0
18. MB253515 15.0% smoothed
19. NACA65-414 a=0.0
20. NACA65-315 a=0.2
21. NACA65-414 a=0.2