DESIGN EQUATIONS. The following section will detail simplified equations for the design of small liquid-fuel rocket motors.
The nomenclature for the motor design is shown in Figure 6. Figure 6 Motor Design Configuration Nozzle The nozzle throat cross-sectional area may be computed if the total propellant flow rate is known and the propellants and operating conditions have been chosen. Assuming perfect gas law theory: Traveling Around the Globe. Through the Air. Science Websites.
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