The “angle of the rearward Mach line,” often denoted as μ2​, represents the angle formed between the Mach line (a type of shock wave) and the direction of the flow after it has been deflected by a certain angle θ. This concept is commonly encountered in the study of compressible fluid dynamics, especially when analyzing […]
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The “angle of the forward Mach line,” often denoted as μ1​, refers to the angle formed between the Mach line (a type of shock wave) and the direction of the incoming flow in compressible fluid dynamics. This angle is crucial in understanding the behavior of shock waves and their interactions with supersonic flows. μ1​ is
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The change in pitching moment (Mα​) due to a change in angle of attack (α) is an important concept in flight mechanics, particularly in the analysis of an aircraft’s stability and control. It refers to how altering the angle of attack affects the forces around the aircraft’s lateral axis, impacting its pitching motion. Mα =u0M
The Prandtl-Meyer angle after a deflection (ν2​) represents the angular deviation of the flow direction due to a change in the flow’s path caused by shock waves, expansion waves, or other flow disturbances. It quantifies the change in the flow’s direction after passing through these waves. ν2​ is the Prandtl-Meyer angle after the deflection. ν1​
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The deflection angle (θ) is an important concept in compressible fluid dynamics that describes the change in direction of a fluid flow caused by the interaction of shock waves or expansion waves. It’s the difference between the Prandtl-Meyer angles (ν) associated with two different Mach numbers (M). The deflection angle provides insight into how a
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The Prandtl-Meyer function, often denoted as ν(M), is a mathematical function used in the study of compressible fluid dynamics, particularly for analyzing the expansion of a flow over a wedge or a curved surface. The function describes the angular deviation of the flow caused by a Mach wave (a type of compression wave) in supersonic
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The Mach number behind the reflected wave, often denoted as M3​, represents the speed of the flow relative to the local speed of sound in the region behind a reflected shock wave. It quantifies the velocity of the flow in relation to the speed at which pressure disturbances propagate through the fluid. Mach number behind
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The “reflected shock to the upper wall angle,” often denoted as Φ, refers to the angle formed between a reflected shock wave and the upper wall of a duct or channel in fluid flow. This concept is commonly encountered in the study of compressible fluid dynamics, particularly in scenarios where shock waves interact with boundaries.Â
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The wave drag coefficient for a wedge is a dimensionless quantity that characterizes the additional drag experienced by an object moving at supersonic speeds due to the formation of shock waves and wave patterns in the airflow around the object. Wave drag is a type of drag that becomes significant as an object approaches or
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The change in the vertical force component (Zα​) due to a change in the angle of attack (α) is a critical concept in flight mechanics and stability analysis. It’s a measure of how altering the angle of attack affects the vertical force acting on an aircraft. Zα = u0 Zw Zα​ represents the change in
