Explanation Determine the stagnation temperature of ideal gas. T 0 = T + V 2 2 c p (I) Here, the static temperature of ideal gas is T , the specific heat of pressure for ideal gas is c p , and the velocity of the ideal gas flow is V . Determine the stagnation pressure of ideal gas. P 0 = P ( T 0 T ) k / ( k − 1 ) (II) Here, the static pressure of ideal gas is P , the specific heat ratio of ideal gas is k . Determine the critical temperature at the throat of nozzle. T ∗ = T 0 ( 2 k + 1 ) (III) Here, the stagnation temperature of air is T 0 . Determine the critical pressure at the throat of nozzle. P ∗ = P 0 ( 2 k + 1 ) k / ( k − 1 ) (IV) Here, the stagnation pressure of air is P 0 . Conclusion: From the Table A-2, “Ideal-gas specific heats of various common gases” to obtain value of specific heat of pressure of helium and the specific heat ratio of helium at 300 K temperature as 5.1926 kJ / kg ⋅ K and 1.667 . Substitute 800 K for T , 100 m / s for V , and 5.1926 kJ / kg ⋅ K for c p in Equation (I). T 0 = ( 800 K ) + ( 100 m / s ) 2 2 × ( 5.1926 kJ / kg ⋅ K ) = ( 800 K ) + ( 100 m / s ) 2 ( 10.3852 kJ / kg ⋅ ° C ) = ( 800 K ) + ( 10000 m 2 / s 2 ) × ( 1 kJ / kg 1000 m 2 / s 2 ) ( 10

CONNECT FOR THERMODYNAMICS: AN ENGINEERI

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Author: CENGEL

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Chapter 17.7, Problem 35P

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The lowest temperature that can be obtained at the throat of the nozzle.

The lowest pressure that can be obtained at the throat of the nozzle.

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Chapter 17.7, Problem 34P

Chapter 17.7, Problem 36P

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Chapter 17 Solutions

CONNECT FOR THERMODYNAMICS: AN ENGINEERI

Ch. 17.7 - A high-speed aircraft is cruising in still air....Ch. 17.7 - What is dynamic temperature?Ch. 17.7 - Prob. 3P Ch. 17.7 - Prob. 4P Ch. 17.7 - Prob. 5P Ch. 17.7 - Prob. 6P Ch. 17.7 - Calculate the stagnation temperature and pressure...Ch. 17.7 - Prob. 8P Ch. 17.7 - Prob. 9P Ch. 17.7 - Prob. 10P

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The lowest temperature that can be obtained at the throat of the nozzle. The lowest pressure that can be obtained at the throat of the nozzle.

Solution Summary: The author determines the stagnation temperature of ideal gas, the specific heat of pressure, and the velocity of the Ideal Gas flow.

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The lowest temperature that can be obtained at the throat of the nozzle. The lowest pressure that can be obtained at the throat of the nozzle.

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The lowest temperature that can be obtained at the throat of the nozzle.

The lowest pressure that can be obtained at the throat of the nozzle.