Author name: Aathif Muzain C

The “inlet area of a compressor” in aircraft design refers to the cross-sectional area through which air or another fluid enters the compressor. This inlet area is a critical design parameter and plays a significant role in determining the performance and efficiency of the compressor. The formula for calculating the inlet area (A_inlet) of a […]

In aircraft design and engineering, “flow rate in a compressor” represents the rate at which a fluid (such as air) is compressed or moved through the compressor. This flow rate is crucial for assessing the performance and efficiency of compressors in aircraft engines and systems. The formula for calculating flow rate in a compressor can

In aircraft design and engineering, a “joule” (symbol: J) is the unit of energy in the International System of Units (SI). It represents the amount of work done or energy transferred when a force of one newton is applied over a distance of one meter in the direction of the force. The formula for calculating

The initial temperature (T_Intial) of a substance or system after a specific heat transfer process can be calculated using the first law of thermodynamics, which accounts for the conservation of energy. The formula for calculating the Initial temperature due to heat transfer can be defined as: Q is the heat energy transferred, typically measured in

The final temperature (T_final) of a substance or system after a specific heat transfer process can be calculated using the first law of thermodynamics, which accounts for the conservation of energy. The formula for calculating the final temperature due to heat transfer can be defined as: Q is the heat energy transferred, typically measured in

In aircraft design and engineering, “temperature change” (ΔT) represents the difference in temperature between two points in a system or the change in temperature of a substance as it undergoes a process. Temperature change is typically measured in degrees Celsius (°C) or Kelvin (K). The formula for calculating temperature change can be defined as: ΔT

In aircraft design and engineering, “mass flow rate” (often denoted as ṁ) represents the rate at which mass flows through a particular point or component in a system, such as the rate at which air flows through an engine’s intake or exhaust. Mass flow rate is a fundamental parameter in fluid dynamics and thermodynamics. The

In aircraft design and engineering, “heat energy” (Q) represents the energy transferred between a system and its surroundings as a result of a temperature difference. Heat energy is a form of energy associated with the random motion of molecules within a substance. The formula for calculating heat energy can be defined as: Heat Energy (Q)

In aircraft design and engineering, “specific heat capacity” (often denoted as c or cp) is a thermodynamic property of a substance that represents the amount of heat energy required to raise the temperature of a unit mass of that substance by one degree Celsius (or one Kelvin). Specific heat capacity is typically measured at constant

In aircraft design and engineering, the “ideal isentropic work done” refers to the work done by a compressor or a turbine operating under ideal and reversible conditions, often referred to as isentropic conditions. This work is associated with the compression or expansion of a fluid (such as air) without losses due to heat exchange or