Propulsion Calculator

The mass flow rate through a convergent nozzle is a crucial parameter in fluid dynamics, especially in the context of compressible flows like those found in rocket nozzles or jet engine exhausts. A convergent nozzle is a geometric configuration where the cross-sectional area of the flow decreases in the direction of the flow. In the […]

The mass flow rate through the nozzle of a turbojet engine is a critical parameter that plays a significant role in the engine’s performance. The nozzle of a turbojet engine is responsible for accelerating the high-velocity, high-temperature exhaust gases generated by the combustion process, ultimately producing thrust. The mass flow rate through the nozzle can

The nozzle mass flow, also known as the mass flow rate through a rocket nozzle, is a crucial parameter in rocket propulsion systems. It represents the rate at which propellant mass is expelled from the rocket engine’s combustion chamber and out through the nozzle. This mass flow rate is directly related to the thrust produced

The pressure-based oxidizer-to-fuel ratio (O/F ratio) is a concept used in combustion and rocket propulsion, particularly in the context of liquid rocket engines. In this approach, the O/F ratio is expressed in terms of the pressures of the oxidizer and fuel. This ratio can be used to monitor and control the combustion process by adjusting

The oxidizer-to-fuel (O/F) ratio for liquid propellant rockets is a fundamental parameter that determines the proportion of oxidizer to fuel used in the rocket’s propulsion system. In liquid rocket engines, the oxidizer and fuel are stored in separate tanks and are combined in a combustion chamber for combustion. Achieving the correct O/F ratio is essential

The oxidizer-to-fuel (O/F) ratio for liquid propellant rockets is a fundamental parameter that determines the proportion of oxidizer to fuel used in the rocket’s propulsion system. In liquid rocket engines, the oxidizer and fuel are stored in separate tanks and are combined in a combustion chamber for combustion. Achieving the correct O/F ratio is essential

The oxidizer-to-fuel (O/F) ratio for liquid propellant rockets is a fundamental parameter that determines the proportion of oxidizer to fuel used in the rocket’s propulsion system. In liquid rocket engines, the oxidizer and fuel are stored in separate tanks and are combined in a combustion chamber for combustion. Achieving the correct O/F ratio is essential

The oxidizer-to-fuel ratio (O/F ratio), also known as the oxygen-to-fuel ratio in some contexts, is a crucial parameter in combustion and propulsion systems. It represents the ratio of the amount of oxidizer (often oxygen or another oxygen-containing compound) to the amount of fuel (the substance that undergoes combustion) used in a combustion process. The O/F

The oxidizer-to-fuel ratio for solid propellant rockets refers to the ratio of the mass of the oxidizer to the mass of the fuel in the solid propellant composition. This ratio is a critical parameter for designing and controlling the performance of solid rocket motors. In solid rocket propellants, both the fuel and oxidizer are intimately

The Tsiolkovsky rocket equation is a fundamental equation in astronautics that describes the relationship between the change in velocity (Δv) a rocket can achieve, the effective exhaust velocity (Ve) of its propulsion system, and the initial and final masses of the rocket. Here’s the Tsiolkovsky rocket equation in SI units Where: Δv is the change