Author name: Arshad Arif A.S

The specific energy equation refers to different equations depending on the context in which it is used.  Where: E is the specific energy (energy per unit mass) Q is the total energy m is the mass

The formula for calculating the pressure in a combustion chamber depends on various factors such as the type of fuel, combustion process, chamber geometry, and operating conditions. However, a simplified formula for idealized combustion processes is the ideal gas law: Where: P is the pressure in the combustion chamber (in Pascals or atmospheres). n is

The exit velocity of a rocket nozzle can be calculated using the ideal rocket equation, which describes the relationship between the velocity of a rocket, the effective exhaust velocity, and the natural logarithm of the ratio of the initial mass of the rocket to its final mass. The formula is as follows: Where: ve​ is

An air-breathing engine thrust refers to the force generated by an engine that ingests air from the atmosphere, mixes it with fuel, combusts the mixture, and expels the resulting exhaust gases to produce propulsion. Where: F is the thrust generated by the engine (in Newtons). m˙ is the mass flow rate of air passing through

The thermal efficiency of a turboprop engine is a measure of how effectively it converts the heat energy from fuel combustion into useful mechanical work. It’s a ratio of the useful work output to the heat input. Where: T2s​ is the temperature at the end of the adiabatic expansion process (isentropic) in the turbine. T1​

The propellant mass fraction density, often denoted as ρprop​, is a measure of the mass of propellant per unit volume. In the context of propulsion systems, especially in aerospace engineering, it refers to the density of the propellant used in rocket engines, thrusters, or other propulsion devices. Where: ρprop​ is the propellant mass fraction density.

Jet velocity density is a measure of the momentum flux per unit area of a fluid jet. It quantifies the kinetic energy per unit volume of the fluid stream. Mathematically, it is defined as the mass flow rate of the jet divided by its cross-sectional area. It is commonly used in fluid dynamics and engineering

Propulsive efficiency density is a metric used to evaluate the efficiency of a propulsion system. It represents the amount of useful propulsive power generated per unit mass flow rate of propellant consumed. In other words, it quantifies how effectively a propulsion system converts the energy stored in its propellant into useful thrust for propulsion. Where:

The formula for calculating the throat area of a nozzle depends on the shape of the nozzle. In the case of a converging-diverging (CD) nozzle, which is commonly used in aerospace engineering. Where: At​ is the throat area, dt​ is the diameter of the throat.

The augmented thrust coefficient density formula typically refers to a formula used in aerospace engineering to calculate the increase in thrust produced by an augmented system, such as afterburners in jet engines. One common formula for augmented thrust coefficient density is: Where: Taug​ is the augmented thrust (thrust produced by the augmentation system). Af​ is the