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For a fixed turbine inlet temperature and static temperature (0) and fixed bypass ratio (B) there exists an optimal compressor (size / inlet temperature

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For a fixed turbine inlet temperature and static temperature (0) and fixed bypass ratio (B) there exists an optimal compressor (size / inlet temperature / pressure ratio / exit velocity) to maximize thrust.

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The statement you provided is generally correct when considering the optimization of a gas turbine engine for aircraft propulsion In the design of a g... blur-text-image

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