Propulsion Calculator

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

The thrust coefficient (Ct) for a turboshaft engine is a dimensionless parameter used to quantify and compare the thrust performance of the engine, considering different operating conditions and design factors. The thrust coefficient is calculated using the following formula: Ct = (T / (ρ * A * V)) Where: Ct is the thrust coefficient (dimensionless).

The thrust coefficient (Ct) for a turbofan engine is a dimensionless parameter used to characterize and compare the thrust performance of the engine, considering various operating conditions. It relates the actual thrust produced by the engine to the engine’s design and the dynamic pressure of the incoming air. The formula for calculating the thrust coefficient

The thrust coefficient (Ct) for a turboprop engine is a dimensionless parameter that characterizes the engine’s thrust performance by relating the actual thrust it produces to the engine’s operating conditions and design. The formula to calculate the thrust coefficient for a turboprop engine is as follows: Ct = (T / (ρ * A * V))

The thrust coefficient (Ct) of a turbojet engine is a dimensionless parameter that characterizes the engine’s thrust performance by relating the actual thrust it produces to the engine’s operating conditions and design. It is calculated using the following formula: Ct = (T / (P * Ae)) Where: Ct is the thrust coefficient (dimensionless). T is

The thrust coefficient, often denoted as Ct, is a dimensionless parameter used to characterize and compare the thrust performance of a propulsion system, typically a jet engine or rocket engine. It relates the actual thrust produced by the engine to the theoretical thrust that could be generated under certain ideal conditions. The formula for calculating

The propulsive efficiency (ηp) of an aerospike engine measures how effectively the engine converts the energy from the combustion of fuel into useful thrust for propulsion. Aerospike engines are a type of rocket engine designed to provide efficient thrust over a range of altitudes. The propulsive efficiency formula for an aerospike engine is as follows: