Author name: Gurupriya Dey Sarkar

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

The thrust coefficient (Ct) for a scramjet engine is a dimensionless parameter used to characterize and compare the thrust performance of the engine under various operating conditions. Scramjet engines operate in the hypersonic flight regime and rely on supersonic combustion of air and fuel. The thrust coefficient is calculated using the following formula: Ct =

The thrust coefficient (Ct) for a ramjet engine is a dimensionless parameter used to characterize and compare the thrust performance of the engine under various operating conditions. The thrust coefficient is calculated using the following formula: Ct = (T / (ρ * A * Vj)) Where: Ct is the thrust coefficient (dimensionless). T is the