The Engine Thrust Deduction Factor represents the fraction of the engine thrust that is not available for accelerating the aircraft, as it is offset by the aerodynamic drag. E is the Engine Thrust Deduction Factor. T is the thrust produced by the engines. D is the total aerodynamic drag acting on the aircraft. W […]
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The thrust for a propeller-driven aircraft represents the relationship between the thrust produced by the propeller, the shaft power provided to the propeller, and the velocity of the aircraft. T: Thrust Pshaft​: Shaft power V: Velocity
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Specific Excess Power (excessPexcess​) is a measure of the surplus power available to an aircraft in climbing flight. P excess​ is the Specific Excess Power, T is the thrust produced by the aircraft’s engines, D is the total drag acting on the aircraft
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Jet Engine Specific Fuel Consumption of a jet engine is a measure of the amount of fuel consumed per unit of thrust produced. SFC is the Specific Fuel Consumption, m˙fuel​ is the mass flow rate of fuel, T is the thrust produced by the jet engine.
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Jet Engine Bypass Ratio is a crucial parameter in the design of jet engines. It represents the ratio of the mass of air that bypasses the engine core BPR is the Bypass Ratio. m˙air​ is the mass flow rate of bypass air. m˙fuel​ is the mass flow rate of fuel.
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The standard rate turn angular velocity is the rate at which an aircraft must rotate around its center of gravity to achieve a standard rate turn ωstandard​: Angular velocity for a standard rate turn g: Acceleration due to gravity (approximately 9.81 m/s²) V: Velocity of the aircraft
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The velocity ratio in a jet engine is commonly expressed as the pressure ratio, which is the ratio of the total pressure at the exit of the combustion chamber (pt3​) to the total pressure at the compressor exit (pt2​). pt3​ is the total pressure at the exit of the combustion chamber pt2​ is the
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The downwash angle (δ) is the angle at which the wake of an aircraft descends due to the influence of the aircraft’s wing V is the induced velocity in the downward direction U is the freestream velocity.
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The critical angle of attack is the angle of attack at which an airfoil or wing experiences a stall. A stall occurs when the airflow over the wing separates, leading to a sudden decrease in lift. αcrit​ is the critical angle of attack, CLmax​​ is the maximum coefficient of lift, π is a mathematical
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Thrust Specific Fuel Consumption (TSFC) is a crucial parameter in aircraft design and is defined as the fuel consumption rate per unit of thrust produced by a jet engine TSFC is the thrust-specific fuel consumption, m˙fuel​ is the fuel mass flow rate, T is the thrust.
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