Dynamic thrust is the net force available to an aircraft, determined by subtracting aerodynamic drag from total propulsion thrust in a specific flight condition. In level flight (T=D), dynamic thrust is zero, while in climb or acceleration (T>D), it’s positive, signifying excess thrust for climbing. Conversely, during descent or deceleration (T<D), it’s negative, indicating the […]
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The Lift-to-Drag ratio is a measure of the efficiency of an aircraft in generating lift compared to the amount of drag it produces. A higher L/D ratio indicates a more efficient aircraft, as it means that the aircraft is producing a greater amount of lift relative to the drag it is experiencing. This ratio is
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Available power in flight mechanics refers to the maximum power that an aircraft’s propulsion system can generate. It represents the total power output available for sustaining flight and overcoming aerodynamic drag. The available power is a key parameter for understanding an aircraft’s performance capabilities, and it is influenced by the efficiency of the engine or
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The thin-walled tube torsion is used to calculate the shear stress in a thin-walled cylindrical structure subjected to torsional loading Ï„ is the shear stress in the thin-walled tube, T is the applied torque (twisting moment), R is the outer radius of the tube, J is the polar moment of inertia of the tube’s cross-section.
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Flow separation refers to the phenomenon where a fluid flow detaches from a surface, typically due to adverse pressure gradients or changes in flow direction. The formula to predict flow separation is complex and depends on various factors such as Reynolds number, surface roughness, and flow conditions. However, one common criterion used to predict flow
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Lift-Off Velocity (VLOF) is the minimum speed an aircraft must reach during the takeoff roll to become airborne. It represents the speed at which the lift generated by the aircraft’s wings becomes equal to the weight of the aircraft, allowing it to overcome gravity and lift off the ground. The formula to calculate Lift-Off Velocity
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The adiabatic flame temperature refers to the maximum temperature achieved during the complete combustion of a fuel in the absence of heat exchange with the surroundings (adiabatic conditions). It represents the highest temperature attainable when all the heat released by the combustion process is retained within the system and is not lost to the surroundings.
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The torsion for a circular shaft expresses the relationship between the applied torque and the resulting shear stress in the material. Ï„ is the shear stress in the circular shaft, T is the applied torque (torque is a twisting force), r is the radial distance from the center of the shaft to the point
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The throat area ratio formula, often used in fluid mechanics, typically refers to the ratio of the cross-sectional area of a throat to the cross-sectional area of a duct or nozzle. It’s commonly denoted as AR and calculated as: Where: At​ is the cross-sectional area of the throat. Ae​ is the cross-sectional area of the
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The shear flow (q) in a beam is a measure of the distribution of shear stress along the cross-section of the beam. q is the shear flow, V is the shear force applied to the section, Q is the first moment of area of the region under consideration, I is the moment of inertia
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