Gases leaving the propulsion nozzle of a rocket are modeled as flowing radially outward from a point upstream from the nozzle throat. Assume the speed of the exit flow, \(V_{e}\), has constant magnitude. Develop an expression for the axial thrust, \(T_{a}\), developed by flow leaving the nozzle exit plane. Compare your result to the one-dimensional approximation, \(T=\dot{m} V_{e}\). Evaluate the percent error for \(\alpha=15^{\circ}\). Plot the percent error versus \(0 \leq \alpha \leq 22.5^{\circ}\).

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R- P4.90 V