| CONCLUSION | ||
The rocket thrust equation is used to calculate the thrust of a rocket and consists of two parts-momentum thrust and pressure thrust. Momentum thrust is, by far, the larger contributor to total thrust. Rocket thrust can be increased by increasing propellant mass flow or by increasing exit velocity with nozzle design or propellant selection. Each method has advantages and disadvantages, and application of the rocket may dictate which method is the best. |
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