Propulsion Calculator

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

The fuel-air ratio, or equivalence ratio (φ), for a High Bypass Ratio turbojet engine is a measure of how the actual fuel-air mixture ratio in the engine compares to the stoichiometric fuel-air mixture ratio. The stoichiometric ratio represents the ideal proportion of fuel and air required for complete combustion. The formula for calculating φ is

Calculating the fuel-air ratio (equivalence ratio, φ) in a turboshaft engine involves determining the ratio of the actual fuel flow rate to the stoichiometric fuel flow rate for a given amount of incoming air. The stoichiometric ratio represents the ideal proportion of fuel and air needed for complete combustion. The formula to calculate φ is

The fuel-air ratio in a turboprop engine, also referred to as the “equivalence ratio” (φ), is a measure of how the actual fuel-air mixture ratio in the engine compares to the stoichiometric fuel-air mixture ratio. The stoichiometric ratio is the ideal proportion of fuel and air required for complete combustion. A φ value of 1

The fuel-air ratio in a turbofan engine, often referred to as the “equivalence ratio” (φ), is a measure of how the actual fuel-air mixture ratio in the engine compares to the stoichiometric fuel-air mixture ratio. The stoichiometric ratio is the ideal proportion of fuel and air required for complete combustion. A φ value of 1

The fuel-air ratio in a turbojet engine, often referred to as the “equivalence ratio” (φ), is a measure of how the actual fuel-air mixture ratio in the engine compares to the stoichiometric fuel-air mixture ratio. The stoichiometric ratio is the ideal proportion of fuel and air required for complete combustion. A φ value of 1

When analyzing the energy transfer within a propulsion system, specific heat can be used to determine the change in enthalpy (ΔH) of the working fluid as it goes through various processes. The change in enthalpy is related to the heat input or output and can be expressed as:ΔH=m∗Cp∗ΔT Where: ΔH is the change in enthalpy

The specific heat is also relevant when calculating the thermodynamic efficiency of a propulsion system, such as a rocket or a jet engine. The efficiency (η) can be calculated using the specific heat at constant pressure (Cp) and the specific heat at constant volume (Cv) as follows: η=1−Cv/Cp​ This equation indicates how efficiently the energy

Specific heat (often denoted as “C”) is a property of a substance that describes its ability to absorb or release heat energy when its temperature changes. It is typically measured in joules per kilogram per degree Celsius (J/kg°C) or in calories per gram per degree Celsius (cal/g°C). Cv is the amount of heat required to