Consider an airfoil flying at a velocity of V∞ = 33 m/s at an angle of attack of a = 3°. Boundary layers form over the upper and lower surfaces of the airfoil. The upper surface of the airfoil is given as Yu/c = (0.13)(x/c)(1-x/c) where the chord length, c = 1.8 m. The local skin friction coefficient along the upper surface is found to vary as Cf u =((1.11)(x/c)1/2 + (-1.45)(x/c)3/2 )x10-3 The flow is laminar over most of the upper surface of the airfoil then abruptly separates at a location, Xsep. Determine the location at which the flow separates on the upper surface of the airfoil. Give your answer to three significant digits. a.) Separation point, Xsep m. The freestream density is given by p∞ = 1.225 kg/m3 and the lower surface of the airfoil is given as yi/c = (-0.13)(x/c)(1-x/c) The local skin friction coefficient along the lower surface of the airfoil is found to vary as Cf1 = ((0.69)(x/c)1/2 )x10-3 Determine the frictional drag per unit span on the airfoil, Dr. Give your answer to three significant digits. b.) Frictional drag per unit span on the airfoil, Df = N/m
Consider an airfoil flying at a velocity of V∞ = 33 m/s at an angle of attack of a = 3°. Boundary layers form over the upper and lower surfaces of the airfoil. The upper surface of the airfoil is given as Yu/c = (0.13)(x/c)(1-x/c) where the chord length, c = 1.8 m. The local skin friction coefficient along the upper surface is found to vary as Cf u =((1.11)(x/c)1/2 + (-1.45)(x/c)3/2 )x10-3 The flow is laminar over most of the upper surface of the airfoil then abruptly separates at a location, Xsep. Determine the location at which the flow separates on the upper surface of the airfoil. Give your answer to three significant digits. a.) Separation point, Xsep m. The freestream density is given by p∞ = 1.225 kg/m3 and the lower surface of the airfoil is given as yi/c = (-0.13)(x/c)(1-x/c) The local skin friction coefficient along the lower surface of the airfoil is found to vary as Cf1 = ((0.69)(x/c)1/2 )x10-3 Determine the frictional drag per unit span on the airfoil, Dr. Give your answer to three significant digits. b.) Frictional drag per unit span on the airfoil, Df = N/m
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Transcribed Image Text:Consider an airfoil flying at a velocity of V0o = 33 m/s at an angle of attack of a = 3°. Boundary layers form over the upper and lower
surfaces of the airfoil. The upper surface of the airfoil is given as
Yu/c = (0.13)(x/c)(1-x/c)
where the chord length, c = 1.8 m. The local skin friction coefficient along the upper surface is found to vary as
Cfu =(( 1.1)(x/c)/2 + (- 1.45)(x/c)3/2 )×10-3
The flow is laminar over most of the upper surface of the airfoil then abruptly separates at a location, Xsep: Determine the location at
which the flow separates on the upper surface of the airfoil. Give your answer to three significant digits.
a.) Separation point, Xsep
m.
%3D
The freestream density is given by po = 1.225 kg/m3 and the lower surface of the airfoil is given as
y/c = (-0.13)(x/c)(1-x/c)
The local skin friction coefficient along the lower surface of the airfoil is found to vary as
Cf1= ((0.69)(x/c)/2 )x10-3
Determine the frictional drag per unit span on the airfoil, Df. Give your answer to three significant digits.
b.) Frictional drag per unit span on the airfoil, Df =
N/m
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