(a) Explanation The figure-(1) represents the control volume of the rocket. Figure-(1) Assume that the flow is steady. Write the integral expression for the thrust developed by the exhaust gas. F = ∫ ρ V 2 ⋅ n ^ d A (I) Here, velocity of the exhaust gas is V , density of the water is ρ , area of the exhaust manifold is A . Write the expression for the elemental area. d A = 2 π r d r Substitute 2 π r d r for d A in Equation (I). F = ∫ ρ V 2 ( 2 π r d r ) = 2 π ρ V 2 ∫ r d r (II) Integrate Equation (II) from the upper limit D 2 to 0 (b) To determine The thrust developed by the exhaust gas.

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ISBN: 9781119571490

Author: GERHART

Publisher: WILEY

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Chapter 5.2, Problem 73P

(a)

To determine

The thrust developed by the exhaust gas is ρAV2.

(b)

To determine

The thrust developed by the exhaust gas.

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Chapter 5.2, Problem 72P

Chapter 5.2, Problem 74P

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The thrust developed by the exhaust gas is ρ A V 2 .

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