In aerodynamics, the taper ratio (often represented as “λ” or “TR”) is a geometric parameter used to describe the shape of a wing, specifically a wing’s planform. The taper ratio is defined as the ratio of the tip chord (“ct”) to the root chord (“cr”) of a wing. “ct” is the tip chord (width) of […]
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The lift coefficient (CL​) for a finite wing is a dimensionless aerodynamic parameter that quantifies the lift generated by the entire wing normalized by the dynamic pressure of the flow and the wing’s reference area. It is a crucial parameter used to characterize the aerodynamic performance and lift generation capability of a finite wing, taking
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The lift coefficient (CL​) for a finite wing is a dimensionless aerodynamic parameter that quantifies the lift generated by the entire wing normalized by the dynamic pressure of the flow and the wing’s reference area. It is a crucial parameter used to characterize the aerodynamic performance and lift generation capability of a finite wing, taking
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he general circulation distribution along an arbitrary finite wing refers to the distribution of circulation (vorticity) along the span of a wing that is not constrained to any specific idealized shape, such as an elliptic or rectangular wing. The circulation distribution provides insights into how lift is generated and distributed across the span of the
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In aerodynamics, “span” refers to the distance between the wingtips of an aircraft or any other lifting surface, such as a wing or a rotor blade. It is a fundamental geometric parameter that characterizes the lateral extent of the lifting surface. Wing span (b) in m Angle (θ) in rad Span distance (y) in m
The chord length (c(y)) of an airfoil section located at an arbitrary spanwise station y is the straight-line distance between the leading edge and the trailing edge of the airfoil, measured perpendicular to the direction of the airflow. It is a fundamental geometric parameter that characterizes the shape and dimensions of the airfoil section at
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The induced angle of attack (αi​) for an elliptic lift distribution is derived based on the lift distribution of an elliptically loaded wing. The elliptic lift distribution is a theoretical idealization commonly used in aerodynamics for its desirable characteristics. It’s a distribution where the lift generated by each spanwise station is proportional to the local
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Induced drag per unit span refers to the amount of induced drag generated by an airfoil section located at an arbitrary spanwise station, normalized by the wing’s span. Induced drag is a type of drag that is associated with the generation of lift by an aircraft’s wings. It occurs due to the creation of wingtip
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Induced drag per unit span refers to the amount of induced drag generated by an airfoil section located at an arbitrary spanwise station, normalized by the wing’s span. Induced drag is a type of drag that is associated with the generation of lift by an aircraft’s wings. It occurs due to the creation of wingtip
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Lift per unit span at an arbitrary spanwise station, often denoted as L′(y0​), refers to the lift generated by an airfoil section located at that specific spanwise position, normalized by the wing’s span. It provides insight into the distribution of lift along the wing’s span and is an essential parameter in aerodynamics. L′(y0​): Lift per
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