Consider the performance of a solid-propellant rocket under conditions that change with time. The stagnation temperature...

 

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Consider the performance of a solid-propellant rocket under conditions that change with time. The stagnation temperature is constant at 3,000 °K. The stagnation pressure changes slowly with time: Þ, = 20 - 0.04 t 0<t<100 for po in MPa and t in seconds. The nozzle has an area ratio of 5 and a throat area of 0.3 m. It exhausts into a vacuum. The fluid man be considered to have y-1.4 and a molecular weight of M= 20 kg/kmol. How do the following vary with time: a.) Exhaust Velocity, b.) Mass Flow Rate, c.) Thrust? Consider the performance of a solid-propellant rocket under conditions that change with time. The stagnation temperature is constant at 3,000 °K. The stagnation pressure changes slowly with time: Þ, = 20 - 0.04 t 0<t<100 for po in MPa and t in seconds. The nozzle has an area ratio of 5 and a throat area of 0.3 m. It exhausts into a vacuum. The fluid man be considered to have y-1.4 and a molecular weight of M= 20 kg/kmol. How do the following vary with time: a.) Exhaust Velocity, b.) Mass Flow Rate, c.) Thrust?

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Given data Stagnchim Pessuve Po 20004t mPa Octeioo Stanonim temperateme To NOzzie ... View the full answer