The Fuel Flow Rate (mË™fuel​) is a critical parameter in aircraft design that represents the rate at which fuel is consumed by the aircraft’s engines mË™fuel​ is the fuel flow rate, T is the thrust produced by the aircraft’s engines, specific fuel consumptionspecific fuel consumption is the amount of fuel consumed per unit of thrust.
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Static Stability Margin represents the distance between the center of gravity and the aerodynamic center normalized by the mean aerodynamic chord. X CG​ is the longitudinal position of the center of gravity, X AC​ is the longitudinal position of the aerodynamic center, cˉ is the mean aerodynamic chord.
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Rolling Resistance Force is the force opposing the motion of an aircraft as it moves along the ground. Frr​ is the rolling resistance force, μrr​ is the coefficient of rolling resistance, W is the weight of the aircraft.
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In flight mechanics, “range” refers to the horizontal distance an aircraft can travel without the need for refueling. It is a crucial performance parameter and is a measure of the endurance and fuel efficiency of an aircraft. Range is typically expressed in units such as nautical miles or kilometers. Mathematically, range can be calculated using
Endurance refers to the ability of an aircraft to remain in flight for a specific duration, considering factors such as fuel consumption, weight, and power requirements. It is a measure of how long an aircraft can sustain level flight with the available fuel resources. To maximize endurance, the aircraft should fly at an airspeed that minimizes
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The Coefficient of Thrust is a dimensionless parameter that quantifies the efficiency of a propeller or rotor in converting power into thrust. A higher CT​ indicates a more efficient conversion of power into thrust, which is desirable for propeller and rotor designs in aviation and other applications. The formula to calculate Coefficient of Thrust as
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The Mach number (Ma) is a dimensionless quantity that characterizes the speed of an object or fluid relative to the speed of sound in the surrounding medium. It indicates whether the flow is subsonic, sonic, or supersonic. Where: Ma is the Mach number. v is the velocity of the object or fluid. c is the
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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
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Total pressure (Pt​), also known as stagnation pressure, is the sum of the static pressure and dynamic pressure in a fluid flow. It represents the total energy per unit volume of a fluid stream, accounting for both the pressure energy and kinetic energy. Total pressure is a crucial parameter in fluid mechanics, particularly in analyzing
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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.
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