The mass-specific impulse (Isp) formula is typically used in the context of rocket propulsion and is calculated as the total impulse divided by the propellant mass expended. Mathematically, it’s represented as: Where: Isp​ is the mass-specific impulse (usually measured in seconds), F is the thrust generated by the rocket (measured in newtons), Δt is the […]
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Thrust specific fuel consumption (TSFC) is a measure of the efficiency of an engine in converting fuel into thrust. It represents the amount of fuel consumed by an engine to produce a unit of thrust over a specific period of time. Where: =TSFC is the thrust specific fuel consumption (units: mass flow of fuel per
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The mass-specific impulse (Isp) formula is typically used in the context of rocket propulsion and is calculated as the total impulse divided by the propellant mass expended. Mathematically, it’s represented as: Where: Isp​ is the mass-specific impulse (usually measured in seconds), F is the thrust generated by the rocket (measured in newtons), Δt is the
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Mass ratio variation refers to the change in the ratio of masses of a system before and after a process, operation, or event. Propulsion systems like rockets or engines undergo mass ratio variation because they consume propellant during operation, leading to changes in the overall mass ratio of the system. Where: mpayload​ is the mass
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Stagnation temperature, also known as total temperature or total pressure temperature, is a thermodynamic property of a fluid flow. It represents the temperature that a fluid would reach if it were brought to rest isentropically (without any loss or gain of heat) from its current state while maintaining its total enthalpy. Where: T is the
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Stagnation pressure, also known as total pressure or pitot pressure, is a thermodynamic property of a fluid flow. It represents the pressure that a fluid would possess if it were brought to rest isentropically (without any losses due to friction or turbulence) from its current velocity. Where: P is the static pressure of the fluid,
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The formula for radiation loss depends on the context, but in general, it can be calculated using the Stefan-Boltzmann Law, which states that the power radiated per unit area of a black body is directly proportional to the fourth power of the body’s absolute temperature (T). Mathematically, it’s expressed as: Where: P is the power
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The formula for vibrational loss typically depends on the specific system or material you’re dealing with. However, a common formula used in the study of vibrational loss is the damping ratio (ζ) multiplied by the natural frequency (ω_n) of the system.Â
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The formula for calculating the divergence angle of a nozzle depends on the specific type of nozzle being used. For a convergent-divergent (CD) nozzle, which is commonly used in rocket propulsion, the divergence angle can be calculated using the following formula: Where: θd​ is the divergence angle, Me​ is the exit Mach number of the
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The convergence angle of a nozzle refers to the angle formed by the converging section of the nozzle where the flow of fluid or gas is compressed and accelerated before being expelled through the nozzle exit. Where: θ is the convergence angle, Ae​ is the exit area of the nozzle, At​ is the throat area
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