Similarly shaped airfoils to NACA 6-H-15
New! Bulk download of polars in Excel format: n6h15.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. NACA65-716 a=0.2
3. NACA65-715 a=0.0
4. NACA65-715 a=0.2
5. NACA 2-H-15
6. NACA66-715 a=0.0
7. EPPLER 344
8. NACA64-716 a=0.2
9. NACA66-715 a=0.2
10. NACA65-616 a=0.2
11. NACA65-615 a=0.2
12. NACA64-716 a=0.0
13. NACA64-715 a=0.0
14. NACA64-715 a=0.2
15. NACA65-717 a=0.2
16. GOE 632
17. NACA66-615 a=0.2
18. NACA65-717 a=0.0
19. NACA66-714 a=0.0
20. NACA66-716 a=0.0
21. AH 83-150 Q