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AERODINÀMICA (Curs Total)
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Say we have an airfoil with leading edge (LE) and trailing edge (TE) located at 1.37 m, respectively. The pressure coefficient distribution in the upper surface of the airfoil is trapezoidal, with in the TE, and the pressure coefficient distribution in the lower surface fits well a sinusoidal function with period equal to 2.12 times the chord, and amplitude 0.29, crossing the ordinate axis in the LE with the maximum possible positive slope. Please, compute the position of the pressure center of the airfoil in % of the chord (with 5 decimals at least; you do not need to put the "%" sign in the box for introducing the result, it only accepts a numerical value; and please, use the comma "," as decimal separator).
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
Say we have an airfoil with leading edge (LE) and trailing edge (TE) located at 0 and 1,84 m, respectively. The pressure coefficient distribution in the upper surface of the airfoil is trapezoidal, with -0,32 constant for all values of between and 63% of the chord, and then ranging linearly from -0,32 at 63% of the chord to 0 at . On the other hand, the pressure coefficient distribution in the lower surface fits well a cosenoidal function with period equal to 0,57 times the chord, and amplitude 0,67, crossing the positive part of the ordinate axis in the leading edge with null slope. Please, compute the value of the airfoil’s global lift coefficient (with 3 decimals; and please, use the comma "," as decimal separator).