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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,
The measured component of the flow velocity is in the top boundary of the control volume, at in the bottom boundary of the control volume, at components are:
where 0.1, and height axis (see image below), you are asked to compute
For this purpose, you can assume that the , , and
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 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
Note: The results are in SI units with 2 decimals and the comma "," is used as decimal separator