Propulsion Calculator

Propellant mass fraction Calculator is a ratio that represents the proportion of propellant mass to the total initial mass of the rocket. Engineers typically calculate it by dividing the mass of the propellant by the total initial mass of the rocket. High PMF values are desirable for achieving greater efficiency and performance in rocket propulsion […]

Nozzle efficiency Calculator. In various engineering applications where fluid flow needs efficient control or acceleration, such as in propulsion systems, hydraulic machinery, and spray nozzles, nozzle efficiency plays a critical role. Nozzle efficiency Calculator quantifies how effectively a nozzle converts available energy into useful kinetic energy, highlighting the nozzle’s performance compared to its theoretical maximum

The thrust coefficient calculator is a fundamental metric in aerospace engineering, serving as a key indicator of the efficiency and performance of propellers and rotors. Essentially, it measures how effectively these components convert power into thrust, crucial for understanding and optimizing propulsion systems. Derived from the ratio of the actual thrust produced by the propulsion

The mass flow rate calculator measures the mass passing through a system’s point per time unit. It calculates mass transfer or transport rate through a specific area or volume. Mass flow rate measures mass movement through a system’s point per time unit. It quantifies mass transfer rate across an area or volume. Fluid dynamics, thermodynamics,

The Tsiolkovsky rocket equation, named after Russian scientist Konstantin Tsiolkovsky, describes the relationship between the mass of a rocket, its velocity, and the exhaust velocity of the propellant it expels. The Tsiolkovsky rocket equation is expressed as: Where: Δv is the change in velocity (delta-v), ve​ is the effective exhaust velocity of the rocket engine,

In rocketry, we use specific impulse (Isp) to quantify the efficiency of a rocket engine, measuring how effectively it utilizes propellant to generate thrust. A higher specific impulse signifies a more efficient engine, producing greater thrust for a given propellant mass. Typically measured in seconds, specific impulse represents the change in momentum per unit mass

In the field of astronautics and aerospace engineering, the rocket equation, also known as the Tsiolkovsky rocket equation, plays a fundamental role in describing the motion of vehicles that utilize rocket propulsion. It establishes a relationship between the velocity of a rocket, the effective exhaust velocity of its propulsion system, and the natural logarithm of

The thrust equation, a fundamental principle in physics and engineering, expresses how a propulsion system’s force relates to the mass flow rate of the propellant and the velocity at which it expels. Mathematically, it states that the system generates thrust by accelerating mass (exhaust gases) in one direction and that the pressure difference between the

The thermal efficiency for a rocket engine is expressed mathematically as: where: ηth​ is the thermal efficiency, Tv​ is the thrust produced by the engine, Vjet​ is the jet velocity, ​ṁp is the mass flow rate of Propellant, hc​ is the specific enthalpy of the fuel.

Aerojet Rocketdyne is a subsidiary of American defense company L3Harris Technologies that manufactures rocket, hypersonic, and electric propulsive systems for space, defense, civil and commercial applications. The thermal efficiency is expressed mathematically as: where: ηth​ is the thermal efficiency, Tv​ is the thrust produced by the engine, Vjet​ is the jet velocity, ​ṁp is the mass flow rate of Propellant, hc​ is the specific enthalpy of the fuel.