The ratio of initial and final pressures in a tank, denoted as “pi/pf,” represents the relationship between the initial pressure (pi) and the final pressure (pf) within a closed container or system. pi: Initial Pressure – This is the pressure at the beginning of a process, such as the pressure inside a tank or a […]
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The height of the nozzle throat, denoted as “h*,” refers to the vertical distance from the nozzle’s centerline to a specific point within the nozzle where the cross-sectional area is at its minimum. In other words, it is the height measurement perpendicular to the nozzle’s centerline at the narrowest point of the nozzle, known as
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The Reynolds number (Re) is a dimensionless parameter used in fluid dynamics to characterize the flow regime of a fluid or gas around an object or through a conduit. It is a fundamental concept in aerodynamics and fluid mechanics. Re: Reynolds number (dimensionless) ρ (rho): Density of the fluid (kg/m³) V: Velocity of the fluid
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The minimum height of the test model centerline above the lower wind tunnel wall, denoted as “h,” refers to the smallest vertical distance between the centerline of the test model and the surface of the lower wall or floor of a wind tunnel. In wind tunnel testing, this parameter is essential for ensuring that the
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Uninstalled Drag Coefficient (CDu): CDu is a dimensionless coefficient that characterizes the aerodynamic drag of an aircraft in its clean or baseline configuration, meaning it has no external attachments, such as external fuel tanks, bombs, or other stores. It represents the resistance force generated by the aircraft’s airframe, including the fuselage, wings, tail, and other
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At,2 (Diffuser Throat Area): This is the cross-sectional area of the throat of the diffuser section of a propulsion system. The diffuser is the component responsible for slowing down and compressing incoming air or propellant flow before it enters the combustion chamber or nozzle. The area of the diffuser throat is an important parameter in
In flight mechanics and aircraft design, the term “fuselage” refers to the central structure of an aircraft that houses the cockpit, passenger or cargo compartments, and other essential components. It is the main body of the aircraft, and its design varies depending on the type and purpose of the aircraft. (CD0)b: This represents the total
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The static pressure at the diffuser throat where the flow is sonic, denoted as p2*, refers to the pressure of the fluid or gas at the point within the diffuser where the flow velocity reaches the speed of sound (Mach 1). This pressure is a critical parameter in fluid dynamics, particularly in compressible flow situations
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This coefficient represents the overall zero-lift drag of the entire aircraft, including contributions from both the wing and the body (fuselage). It characterizes the inherent drag of the aircraft when it is at zero angle of attack (not generating lift) and is in level, unaccelerated flight. (CD0)wb: This represents the total zero-lift drag coefficient of
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Thrust Required During Level Flight: This is the force or thrust that the aircraft’s engines must produce to balance the forces acting on the aircraft in level flight. In level flight, there are several forces acting on the aircraft. Tt: This represents the thrust required during level flight. It’s the amount of thrust needed to
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