The wing angle of attack, often denoted as 𝛼, is a fundamental parameter in aerodynamics and aviation. It refers to the angle between the chord line of an airfoil (typically a wing or airfoil section) and the oncoming freestream airflow. The chord line is an imaginary straight line connecting the leading edge and trailing edge […]
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Linearized theory for the wave-drag coefficient is an analytical approach used in aerodynamics to estimate wave drag contributions in supersonic and hypersonic flows. It provides a simplified and linear approximation of the wave-drag coefficient (CD) based on certain assumptions. This linearization is valuable for quick estimations and initial design considerations. Wave-drag coefficient (cd) Freestream Mach
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It is defined as the angle between the chord line of the airfoil and the direction of the oncoming air. α: Angle of Attack The angle of attack (α) is the angle between the oncoming air (relative wind) and the chord line of an airfoil (e.g., wing, airfoil, or other lifting surfaces) on an aircraft.
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The wave-drag coefficient (cd) for the supersonic flow over a flat plate is a dimensionless parameter that quantifies the wave drag experienced by the flat plate when it is subjected to a supersonic fluid flow. Wave drag is a significant component of drag in supersonic and hypersonic flows and arises due to the formation of
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The lift coefficient (cl) for supersonic flow over a flat plate is a parameter that quantifies the lift or normal force generated by the flat plate when it is subjected to a supersonic fluid flow. This coefficient is specifically used to characterize the lift forces experienced by the flat plate in a supersonic flow regime,
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The drag coefficient (cd) for a flat plate with the assumption of a small angle of attack is a parameter that quantifies the drag or resistance to motion experienced by the flat plate when it is subjected to a fluid flow and the angle of attack (𝛼) is relatively small. This assumption is often used
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The lift coefficient (cl) for a flat plate with the assumption of a small angle of attack is a parameter that quantifies the lift generated by the flat plate when it is subjected to a fluid flow and the angle of attack (𝛼) is relatively small. This assumption is often used to simplify the analysis
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The normal force coefficient for a flat plate, often denoted as cn, is an aerodynamic parameter used to describe the lift or normal force generated by a flat plate in a fluid flow field. It quantifies how much lift is produced by the flat plate when it is subjected to an oncoming flow. The normal
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The pressure coefficient on the upper surface of a flat plate, denoted as Cp,u, is an aerodynamic parameter used to describe the pressure distribution over the upper surface of the flat plate in a fluid flow field. This parameter quantifies how the local pressure at any point on the upper surface of the flat plate
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The pressure coefficient for linearized supersonic flow over an airfoil, used to describe the local pressure distribution on the surface of an airfoil when it is operating in a supersonic flow regime. This parameter is particularly relevant when analyzing and designing airfoils for supersonic flight. In supersonic flow, the pressure distribution around an airfoil can
