Author name: Gurupriya Dey Sarkar

The thrust coefficient for a turbofan engine is a dimensionless parameter that characterizes the efficiency of the engine in converting fuel into thrust. Turbofan engines are a type of jet engine commonly used in aviation, known for their high bypass ratio compared to turbojet engines. The thrust coefficient is defined as the ratio of the […]

The thrust coefficient for a turbojet engine is a dimensionless parameter that relates the thrust produced by the engine to the dynamic pressure of the incoming air. It is a measure of the efficiency of the propulsion system in converting fuel into thrust. The thrust coefficient is defined as the ratio of the thrust force

The thrust coefficient of an aircraft is a dimensionless parameter that relates the thrust produced by the aircraft’s propulsion system to the dynamic pressure of the incoming air. It is commonly used in aerodynamics to quantify the efficiency of the propulsion system. The thrust coefficient is defined as the ratio of the thrust force produced

A Pressure-Fed Engine is a type of rocket engine where the propellants are forced into the combustion chamber using pressurized tanks. Pressure-fed engines are often used in small-scale rocket systems, where the simplicity of the feed system is advantageous. The pressure is usually provided by high-pressure gas stored in tanks, and the propellants are forced

A Stirling engine is a heat engine that operates on the Stirling cycle, a closed thermodynamic cycle. It works by cyclically compressing and expanding a working fluid (usually a gas) at different temperature levels. The thrust force is not typically associated with Stirling engines, as they are not used for propulsion like rocket engines or

Cryogenic rocket engines use cryogenic propellants, which are gases or liquids that exist at extremely low temperatures. The most common cryogenic propellants are liquid oxygen (LOX) and liquid hydrogen (LH2). Cryogenic rocket engines are commonly used in space exploration due to the high energy content and efficiency of cryogenic propellants. The low temperatures help increase

Microwave Thermal Rocket Engines are a theoretical concept that involves using microwaves to heat a propellant, typically hydrogen, and then expelling the heated propellant to generate thrust. The thrust force in a Microwave Thermal Rocket Engine can be described using a modified version of the rocket thrust equation. This concept is more complex than traditional

Steam rocket engines are a type of rocket propulsion that uses steam as a propellant. The principle behind steam rockets involves heating water to produce steam, and the high-pressure steam is expelled to generate thrust. Steam rocket engines are generally considered experimental and are not as common as other types of rocket engines. They may

Electrostatic Ion Thrusters, commonly known as ion thrusters or electrostatic ion propulsion systems, use electric fields to accelerate ions and generate thrust. The thrust force in an electrostatic ion thruster can be described using the basic rocket thrust equation with some modifications to account for the electrostatic acceleration. Electrostatic ion thrusters are known for their

Nuclear Thermal Electric Propulsion (NTEP) is a theoretical concept that involves using a nuclear thermal reactor to produce high-temperature propellant to generate electricity for an electric propulsion system, such as an ion thruster. The thrust force in an NTEP system can be described using a modified version of the rocket thrust equation. The specific equations