NACA63A315


NACA 63A-315
Direct link: NACA63A315
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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Lift curve slopes of basic Javafoil data for NACA63A315, smooth airfoil:


Re: 500k | 1M | 3M | 6M | 12M

Re = 500k | 1M | 3M | 6M | 12M



Re = 1M | 500k | 3M | 6M | 12M



Re = 3M | 500k | 1M | 6M | 12M



Re = 6M | 500k | 1M | 3M | 12M



Re = 12M | 500k | 1M | 3M | 6M