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Architecture of Computing Systems (Lecture Notes in Computer ...

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220 M.Y. Qadri, D. Matichard, and K.D. McDonald Maier<br />

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Turb<strong>in</strong>e thermodynamics (4->5)<br />

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Turb<strong>in</strong>e Pressure Ratio<br />

Nozzle thermodynamics (5->6)<br />

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�� �� ����� ��� � 518.6 � 3.56 ��������<br />

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.<br />

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�� � � 389.98 ,<br />

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� 473.1376<br />

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�� � � 391.625 . ��������������<br />

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��0 � 51.96896 � � ���<br />

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Turb<strong>in</strong>e Work Per Mass Of Airflow,<br />

where ηt is the turb<strong>in</strong>e efficiency and<br />

cp is the specific heat.<br />

Nozzle Pressure and temperature<br />

ratios<br />

Exit velocity, where ηn is the nozzle<br />

efficiency<br />

Output calculations<br />

Mach Number, where V0 is the<br />

aircraft speed, a0 is the speed <strong>of</strong><br />

sound and R is the gas constant<br />

,<br />

,<br />

Stratospheric Temperature and<br />

pressure for altitude < 36152 feet<br />

Stratospheric Temperature and<br />

pressure for 36152< altitude < 82345<br />

feet<br />

Stratospheric Temperature and<br />

pressure for altitude > 82345<br />

feet

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