Consider an airfoil flying at a velocity of V.. = 31 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 = 2.6 m. The local skin friction coefficient along the upper surface is found to vary as Cf u =( (1.04)(x/c)-1/2 + (- 1.49)(x/c) )× 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 The freestream density is given by po. = 1.225 kg/m³ and the lower surface of the airfoil is given as y₁/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 = ((0.71)(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, D₁ = m. N/m

Consider an airfoil flying at a velocity of V.. = 31 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 = 2.6 m. The local skin friction coefficient along the upper surface is found to vary as Cf u =( (1.04)(x/c)-1/2 + (- 1.49)(x/c) )× 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 The freestream density is given by po. = 1.225 kg/m³ and the lower surface of the airfoil is given as y₁/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 = ((0.71)(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, D₁ = m. N/m

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

Handwriting not allow please

Consider an airfoil flying at a velocity of V.. = 31 m/s at an angle of attack of a = 3º. 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 = 2.6 m. The local skin friction coefficient along the upper surface is found to
vary as
Cf u =((1.04)(x/c)-1/2 + (- 1.49)(x/c) )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
y₁/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
Cfl = ((0.71)(x/c)-1/2)×10-3
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, D
=
N/m

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