Compute the total circulation around a symmetrical airfoil whose circulation distribution is given by eqn. 4.24. Then compute th
e sectional lift of the airfoil using the Kutta- Joukowski theorem.
2 answers:
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Answer:
Explanation:
First we calculate the mass of the aire inside the rigid tank in the initial and end moments.
(i could be 1 for initial and 2 for the end)
State1
State2
So, the total mass of the aire entered is
At this point we need to obtain the properties through the tables, so
For Specific Internal energy,
For Specific enthalpy
For the second state the Specific internal Energy (6bar, 350K)
At the end we make a Energy balance, so
No work done there is here, so clearing the equation for Q
The sign indicates that the tank transferred heat<em> to</em> the surroundings.
possible Answers:
Compensate ⭐⭐⭐⭐⭐
Adjust ⭐⭐⭐⭐⭐
regulate ⭐⭐⭐⭐
tune ⭐⭐⭐
calibrate ⭐⭐⭐
balance ⭐⭐
correct ⭐
