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Consider a 2D airfoil of chord 0.5 m, flying in open atmosphere with veloci...

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Consider

a 2D airfoil of chord

0.5 m, flying in open atmosphere with

velocity

= 87 m/s, as shown in the image

below.

The pressure far downwind becomes uniform and

equal in value to the pressure far upwind,

which is the pressure of the steady atmosphere, also uniform and known: =101325 Pa.

The measured component of

the

flow velocity is

far downwind, and

in the top

boundary of the control volume, at

, and

the bottom boundary of the control volume, at

. These

components are:

where

, , and are known constants, with

0.1,

2.51 m, and 8.19 m, and ^(1/4). For the control volume of length

and height

, symmetric respect to the axis and

axis (see image

below), you are asked to compute

the lift on the obstacle .

For

this purpose, you can assume that the

, ,

, and

. The air density far upwind is known: = 1.097 kg/m³.

Bear

in mind that the velocity cannot be assumed to be horizontal far

upwind and far downwind, while

it is horizontal in the top and bottom boundaries of the

control volume at

and , respectively. The velocity has the following unknown

axis velocity component

far

upwind:

and the following unknown axis velocity far downwind:

Finally, a

ssume

an unknown velocity in the form

for

all the points of the fluid domain where the velocity is unknown, with

being unknowns and .

Note: The results are in SI units with 2 decimals and the comma "," is used as decimal separator

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