In flight mechanics, the “number of cycles” refers to the count of complete oscillation cycles experienced by an aircraft or a specific component during a given time interval. N represents the number of cycles completed during a certain time interval. t is the time interval for which you’re calculating the number of cycles. P is […]
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The “time period of oscillation” usually refers to the time it takes for a system to complete one full cycle of oscillation. In the context of flight mechanics, it could refer to various oscillatory motions and vibrations experienced by aircraft. P = 2Ï€ / ω P is the period of the oscillation, which is the
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The Normal Mach number behind a shock wave, often denoted as Mn,2​, represents the Mach number of the flow behind the shock wave, considering the normal component of velocity relative to the shock’s front. It is used to describe the change in velocity due to a shock wave’s effect on the flow. Normal Mach number
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“complex root” refers to a solution of a characteristic equation that involves complex numbers. λ = η + i λ is the eigenvalue of the system. η represents the real part of the eigenvalue, which affects the rate of decay or growth of the response. ω is the imaginary part of the eigenvalue, representing the
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The change in pitch rate, often referred to as angular velocity around the lateral axis, is a measure of how fast an aircraft’s nose rotates around its side-to-side axis. This rotation corresponds to changes in the aircraft’s pitch attitude. In flight mechanics, pitch rate is an essential parameter that describes the aircraft’s response to control
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The change in moment (torque) around the aircraft’s longitudinal axis, often referred to as the “roll axis,” is related to the aerodynamic behavior of an aircraft’s roll due to changes in angle of attack and other parameters. Mw​ is the change in moment around the longitudinal axis (newton-meter, N·m). Q is the dynamic pressure
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The pressure at the stagnation point, often denoted as ps​, refers to the pressure that a fluid experiences when it is brought to a complete stop in a flow field, typically due to an obstacle or surface. The stagnation point is where the fluid velocity is zero, and it’s also known as the “stagnation point
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In a Pitot tube, the flow velocity (u1​) refers to the velocity of the fluid in a subsonic flow field at a specific point where the Pitot tube is positioned. The Pitot tube is a device used to measure the total pressure of a flowing fluid. In subsonic flow, the velocity of the fluid is
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The Mach number ahead of a wave in a subsonic compressible flow, often denoted as M1​, refers to the ratio of the velocity of the flow ahead of the wave to the local speed of sound in that region. It characterizes how fast the flow is moving relative to the speed of sound, and it’s
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The Mach number behind an oblique shock wave, often denoted as M2​, represents the ratio of the velocity of the flow behind the shock to the local speed of sound in that region. It’s a crucial parameter in the analysis of compressible fluid dynamics and shock waves, particularly in situations where the flow undergoes abrupt
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