00:01
We check the question from the test book.
00:02
Explanation of the solution is, the figure one, it presents the control volume of the rocket.
00:08
This is the figure one for the question.
00:13
And assuming that the flow is steady, writing the integral expression for the thrust developed by the exhaust gas.
00:19
F is equal to integration, row v to n -cab, d, l, this p, equation 1.
00:23
Here, velocity of the exhaust gas is v, density of the water is row area of the exhaust manifold is capital a, writing the expression for elemental area, d .a is equal to by r, dr.
00:32
Substituting this value for da in equation 1 we get f is equal to let this be equation 2 integrating equation 2 from upper limit d2 to 0 we get f is equal to let this be equation 3 and substituting the value in equation 4 we get f is equal to row a f is equal to row a v2 thus the thrust developed is row a v2 conclusion is the thrust developed by the exhaust gas is row a v2 this is the answer for the first question and the next question is the expression of the solution is the figure 2 represents the control volume of the rocket...