The Merlin 1D on Falcon 9 uses LOX/Kerosene as propellants. The molecular weight and specific heat...

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The Merlin 1D on Falcon 9 uses LOX/Kerosene as propellants. The molecular weight and specific heat ratio of the combustion products can be estimated as M = 21.6 g/mol and y = 1.2. The chamber pressure is 10.8 MPa and the combustion temperature is 3573 K. If the throat area is 0.1 m, determine the thrust for the following conditions: Ambient pressure MPa Psia Exhaust area, m 1 0 0 0.1 2 0 0 4.06 3 0.101 14.7 0.1 4 0.101 14.7 4.06 The Merlin 1D on Falcon 9 uses LOX/Kerosene as propellants. The molecular weight and specific heat ratio of the combustion products can be estimated as M = 21.6 g/mol and y = 1.2. The chamber pressure is 10.8 MPa and the combustion temperature is 3573 K. If the throat area is 0.1 m, determine the thrust for the following conditions: Ambient pressure MPa Psia Exhaust area, m 1 0 0 0.1 2 0 0 4.06 3 0.101 14.7 0.1 4 0.101 14.7 4.06