Author name: Arshad Arif A.S

The formula for engine performance curves varies depending on the type of engine and the specific parameters being considered. However, a common formula used to represent engine performance curves is: Where: P is the power output of the engine, T is the torque generated by the engine, and ω is the angular velocity (rpm) of […]

The combustion stability margin (CSM) is a measure used in rocket propulsion to assess the stability of combustion in the engine. It is often expressed as a ratio of the chamber pressure oscillation amplitude to the mean chamber pressure. Where: A is the amplitude of chamber pressure oscillations. ⟨P⟩ is the mean chamber pressure.

The propellant mixing ratio formula is used in rocket propulsion to determine the ratio of oxidizer to fuel required for combustion. It’s typically expressed as the mass ratio of oxidizer to fuel. The formula is: ​​Where: mox​ is the mass of oxidizer. mfuel​ is the mass of fuel

The formula for acoustic modes in a resonant cavity, such as a pipe or a drum, depends on the geometry and boundary conditions of the cavity. For a cylindrical pipe with length L, the formula for the frequency f of the n-th acoustic mode is: Where: c is the speed of sound in the medium

Oscillation frequency is the number of complete cycles of a periodic motion that occur in a unit of time, usually measured in hertz (Hz), representing the rate of repetition of the oscillatory behavior. T represents the period of oscillation, which is the time it takes for one complete cycle of the oscillation. Oscillation frequency refers

Propellant utilization involves efficiently using the propellant (fuel and oxidizer) of a rocket to achieve a specific mission objective, typically delivering a payload to a desired destination. Where: Propellant utilization (PU) expresses the efficiency of propellant usage as a percentage. mpayload The mass of the payload (the payload carried by the rocket) constitutes mpropellant​ is

Engineers use film cooling to shield surfaces from high temperatures, often in applications with combustion gases or hot fluids. It involves the introduction of a thin layer of cooler fluid (commonly air or a fuel-rich mixture) over the surface to create a protective barrier. Where: Ts​ is the temperature of the surface being cooled, Tw​

Thrust chamber cooling refers to the process of managing and dissipating the immense heat generated within the combustion chamber of a rocket engine during operation. Where: Q˙​regen​ is the rate of heat transfer per unit length of the chamber. Tchamber​ is the temperature of the combustion chamber wall. Tcoolant,in​ is the temperature of the coolant

To calculate the temperature of a chamber, you typically need to consider various factors such as the heat input, heat loss, and the properties of the materials involved. The general formula for calculating temperature change involves the equation: Where: Q is the heat energy transferred (in Joules or calories), m is the mass of the