Propulsion Calculator

The performance of a scramjet (supersonic combustion ramjet) engine is typically characterized by key parameters that assess its efficiency and effectiveness in generating thrust. Scramjet engines are designed for high-speed flight in the supersonic and hypersonic regimes. The performance of a scramjet engine can be evaluated using various metrics, including specific thrust, thermal efficiency, and […]

The performance of a scramjet (supersonic combustion ramjet) engine is typically characterized by key parameters that assess its efficiency and effectiveness in generating thrust. Scramjet engines are designed for high-speed flight in the supersonic and hypersonic regimes. The performance of a scramjet engine can be evaluated using various metrics, including specific thrust, thermal efficiency, and

The performance of a scramjet (supersonic combustion ramjet) engine is typically characterized by key parameters that assess its efficiency and effectiveness in generating thrust. Scramjet engines are designed for high-speed flight in the supersonic and hypersonic regimes. The performance of a scramjet engine can be evaluated using various metrics, including specific thrust, thermal efficiency, and

The performance of a ramjet engine is typically characterized by key parameters that assess its efficiency and effectiveness in generating thrust. The performance of a ramjet engine can be evaluated using various metrics, including specific thrust, thermal efficiency, and overall thrust. The overall thrust generated by a ramjet engine is the primary performance metric and

The performance of a ramjet engine is typically characterized by key parameters that assess its efficiency and effectiveness in generating thrust. The performance of a ramjet engine can be evaluated using various metrics, including specific thrust, thermal efficiency, and overall thrust. The specific thrust (TS) is a measure of how much thrust is generated per

In the context of propulsion, the specific heat ratio (γ) is a thermodynamic property of the working fluid (usually air or exhaust gases) and is used to describe how the specific heat at constant pressure (Cp) relates to the specific heat at constant volume (Cv). It is a crucial parameter in the analysis of compressible

The chamber pressure required for combustion in a turbofan engine is a key parameter in engine design and operation. This pressure is necessary to drive the combustion process and generate thrust. To calculate the chamber pressure in a turbofan engine, you can use the ideal gas law while considering the specific gas constant (R), absolute

The chamber pressure required for combustion in a turboshaft engine is also an essential parameter for engine design and operation. You can calculate it using the ideal gas law and consider specific gas constant (R), absolute temperature (Tc), mass flow rate (m_dot), cross-sectional area (A), and combustion efficiency (η). The formula for chamber pressure in

The chamber pressure required for combustion in a turboprop engine is an important parameter for engine design and operation. It can be calculated using the ideal gas law while considering specific gas constant (R), absolute temperature (Tc), mass flow rate (m_dot), cross-sectional area (A), and combustion efficiency (η). The formula for chamber pressure in a

A high-bypass ratio turbojet engine is a type of jet engine commonly used in commercial aircraft, and it is known for its superior fuel efficiency compared to low-bypass ratio engines. The bypass ratio is a key parameter that characterizes the engine’s efficiency in terms of thrust production and fuel consumption. Fuel efficiency in the context