The fuel flow rate in the context of aircraft design refers to the rate at which fuel is consumed by the aircraft’s engines to generate the required power for flight mË™fuel​ is the fuel flow rate, P req​ is the power required by the aircraft, and E fuel​ is the energy content of the […]
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The lift coefficient (CL​) for an airfoil section is a critical parameter in aircraft design, representing the effectiveness of the airfoil in generating lift CL section​​ is the lift coefficient for the airfoil section. α is the angle of attack αL0​​ is the zero-lift angle of attack. 2π represents the lift-curve slope
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The jet thrust equation is a fundamental formula used in aircraft design to describe the thrust produced by a jet engine. F is the thrust produced by the jet engine. m˙ is the mass flow rate of the exhaust gases expelled by the engine. Ve​ is the effective exhaust velocity. V0​ is the velocity of
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Power required for level flight is a crucial parameter in aircraft design, representing the amount of power needed to maintain a steady, level flight condition. Preq​ is the power required for level flight, T is the thrust, V is the velocity of the aircraft, and η is the overall efficiency of the propulsion system.
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The Total Pressure Recovery Factor quantifies how well an intake system is able to recover the total pressure of the incoming air. A high total pressure recovery indicates a more efficient intake system, which is crucial for optimal engine performance. R is the Total Pressure Recovery Factor. Pt​ is the total pressure at the inlet.
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The Mach angle is a geometric angle that describes the angle between the direction of an object moving through a fluid (like an aircraft) and the Mach cone, which is a shock wave created by the object when it moves through the fluid at a speed greater than the speed of sound. θ is the
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The rate of climb is a performance parameter used in aircraft design and aviation to describe the vertical speed at which an aircraft can ascend. It is commonly denoted as ROC and is expressed in feet per minute (ft/min) or meters per second (m/s). T is the thrust generated by the aircraft’s engines, D is
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The Static Margin is a measure of the longitudinal stability of an aircraft. It represents the distance between the center of gravity  and the aerodynamic center  normalized by the mean aerodynamic chord SM is the static margin, Xcg​ is the location of the aircraft’s center of gravity, Xac​ is the location of the aerodynamic center,
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Potential energy is the energy an object possesses due to its position or state. In the context of aircraft design, potential energy is often associated with the aircraft’s altitude above a reference point, such as the Earth’s surface or a specified datum. PE is the potential energy, m is the mass of the object, g
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The groundspeed (GS) of an aircraft is the horizontal speed of the aircraft relative to the Earth’s surface. It is the speed at which an aircraft is actually moving over the ground. The groundspeed is a crucial parameter in navigation and flight planning. GS is the groundspeed, TAS is the true airspeed of the
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