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7.22. The rocket motor sketched in Fig. 7.27 has the nozzle bolted to the combustion chamber. From the data below calculate (a) the thrust of the rocket motor and (b) the force (compressive or tensile) at the joint between the nozzle and combustion chamber. The flow rate is 200 lbm/s. Point 1 Point 2 Cross-sectional area, ft² Nozzle 5 30 Pressure, psia Velocity, ft/s 300 Combustion chamber 14.7 Note: The fuel is stored in the combustion chamber. 300 3000 FIGURE 7.27

7.22. The rocket motor sketched in Fig. 7.27 has the nozzle bolted to the combustion chamber. From the data below calculate (a) the thrust of the rocket motor and (b) the force (compressive or tensile) at the joint between the nozzle and combustion chamber. The flow rate is 200 lbm/s. Point 1 Point 2 Cross-sectional area, ft² Nozzle 5 30 Pressure, psia Velocity, ft/s 300 Combustion chamber 14.7 Note: The fuel is stored in the combustion chamber. 300 3000 FIGURE 7.27

Applications and Investigations in Earth Science (9th Edition)
Applications and Investigations in Earth Science (9th Edition)
9th Edition
ISBN:9780134746241
Author:Edward J. Tarbuck, Frederick K. Lutgens, Dennis G. Tasa
Publisher:Edward J. Tarbuck, Frederick K. Lutgens, Dennis G. Tasa
Chapter1: The Study Of Minerals
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## Rocket Motor Analysis ### Problem Statement The rocket motor shown in Figure 7.27 has a nozzle bolted to the combustion chamber. Use the data below to calculate: (a) The thrust of the rocket motor (b) The force (compressive or tensile) at the joint between the nozzle and the combustion chamber. The flow rate is 200 lbm/s. ### Data Table | **Cross-sectional area, ft²** | **Pressure, psia** | **Velocity, ft/s** | |-------------------------------|--------------------|--------------------| | **Point 1** | 5 | 300 | 300 | | **Point 2** | 30 | 14.7 | 3000 | **Note:** The fuel is stored in the combustion chamber. ### Diagram Description **Figure 7.27** illustrates a rocket motor with: - A **combustion chamber** where fuel is stored. - A **nozzle** attached to the combustion chamber, through which exhaust gases are expelled. Identified points: 1. **Point 1** is located at the combustion chamber. 2. **Point 2** is located at the nozzle exit. These points are marked to indicate where the measurements for cross-sectional area, pressure, and velocity are taken. The diagram reflects the typical setup for a rocket motor where the combustion of the fuel results in high-speed exhaust gases being expelled through the nozzle to produce thrust.
Transcribed Image Text:## Rocket Motor Analysis ### Problem Statement The rocket motor shown in Figure 7.27 has a nozzle bolted to the combustion chamber. Use the data below to calculate: (a) The thrust of the rocket motor (b) The force (compressive or tensile) at the joint between the nozzle and the combustion chamber. The flow rate is 200 lbm/s. ### Data Table | **Cross-sectional area, ft²** | **Pressure, psia** | **Velocity, ft/s** | |-------------------------------|--------------------|--------------------| | **Point 1** | 5 | 300 | 300 | | **Point 2** | 30 | 14.7 | 3000 | **Note:** The fuel is stored in the combustion chamber. ### Diagram Description **Figure 7.27** illustrates a rocket motor with: - A **combustion chamber** where fuel is stored. - A **nozzle** attached to the combustion chamber, through which exhaust gases are expelled. Identified points: 1. **Point 1** is located at the combustion chamber. 2. **Point 2** is located at the nozzle exit. These points are marked to indicate where the measurements for cross-sectional area, pressure, and velocity are taken. The diagram reflects the typical setup for a rocket motor where the combustion of the fuel results in high-speed exhaust gases being expelled through the nozzle to produce thrust.
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