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Learn more about Bing search results hereOrganizing and summarizing search results for youTo calculate specific thrust, you can use the following methods 1 2 3 4 5:
- Divide the thrust created by the engine by the mass flow rate of the air.
- Use the formula: Specific Thrust (Fs) = (1 + mf) * Ve - V0, where F is the net thrust, m is the air flow rate, mf is the fuel-air ratio, Ve is the nozzle exit velocity, and V0 is the free stream velocity.
- Calculate the difference between the exit velocity of the exhaust gases and the flight speed (Isp = Ve - V).
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WEBMay 13, 2021 · Dividing the thrust required by the specific thrust tells us how much airflow our engine must produce and this determines the physical size of the engine. There is a similar efficiency parameter called the …
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WEBJun 24, 2024 · The result of our thermodynamic analysis is a certain value of specific impulse. The rocket weight will define the required value of thrust. Dividing the thrust required by the specific impulse will tell us …
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WEBMay 13, 2021 · Why are we interested in specific impulse? First, it gives us a quick way to determine the thrust of a rocket, if we know the weight flow rate through the nozzle. Second, it is an indication of engine efficiency. …
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WEBMay 13, 2021 · On this slide we have gathered together all of the equations necessary to compute the theoretical thrust for a turbojet engine. The general thrust equation is given just below the graphic in the specific …
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WEBTo find the thrust we need to find the ratio of the temperature at exit and the temperature at inlet. This is given by where is the stagnation temperature ratio across the combustor (burner).
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