Author name: Gurupriya Dey Sarkar

The thrust force of an aircraft can be defined as the forward force generated by its propulsion system, which is responsible for propelling the aircraft through the air. The thrust force is a critical component for overcoming aerodynamic drag and enabling the aircraft to achieve and maintain controlled flight. The thrust equation using control volume […]

The thrust force of an aircraft can be defined as the forward force generated by its propulsion system, which is responsible for propelling the aircraft through the air. The thrust force is a critical component for overcoming aerodynamic drag and enabling the aircraft to achieve and maintain controlled flight. The thrust equation using control volume

Cryogenic rocket engines use cryogenic propellants, typically liquid oxygen (LOX) and liquid hydrogen (LH2), which are stored at extremely low temperatures. The thrust is generated by the combustion of these cryogenic propellants in the rocket engine. If you have specific data on thrust, burn time, and the mass of cryogenic propellant consumed during the operation

Microwave thermal rocket engines operate by using microwave energy to heat a propellant, such as hydrogen, to generate thrust. The thrust is produced by the expulsion of the heated propellant. The mass flow rate of the propellant and the effective exhaust velocity determine the specific impulse. If you have specific data on thrust, burn time,

For a steam rocket engine, the thrust is generated by the expulsion of steam produced by heating a liquid propellant (typically water) through a combustion process. The mass flow rate (�˙m˙) of the propellant and the effective exhaust velocity determine the specific impulse. If you have specific data on thrust, burn time, pressure at the

Ion thrusters operate by accelerating ions to high velocities using electric fields. The thrust is generated by the expulsion of these accelerated ions. The mass flow rate of the propellant and the exhaust velocity are key parameters influencing the specific impulse. If you have specific data on thrust, burn time, and the mass of propellant

A photonic laser thruster, also known as a laser propulsion system, is a theoretical concept that involves using directed laser energy to propel a spacecraft. In such a system, a laser beam is used to transfer momentum to a spacecraft by reflecting off a reflective surface on the spacecraft. For a photonic laser thruster, the

Nuclear Thermal Electric Propulsion (NTEP) refers to a type of electric propulsion system that uses nuclear thermal energy to generate electricity, which is then used to power electric thrusters. For NTEP, the specifics of the nuclear reactor design, the thermodynamic cycle used to convert thermal energy to electricity, and the electric propulsion system all play

Liquid flyback booster rocket engines are designed to be part of a reusable launch system where the booster stage returns to Earth for recovery and reuse. These engines are typically used in the initial stage of a rocket launch. To calculate the specific impulse for a specific liquid flyback booster rocket engine, you would need

Laser thermal rocket engines are theoretical propulsion systems that involve the use of directed energy from lasers to heat a propellant, typically a working fluid such as hydrogen. The heated propellant is then expelled through a rocket nozzle to generate thrust. For laser thermal rocket engines, factors such as the laser power, absorption efficiency, heating