True Airspeed” (TAS) refers to the actual speed of an aircraft through the surrounding air. It is the speed of the aircraft relative to the undisturbed air in which it is flying, and it is measured in knots (nautical miles per hour) or meters per second (m/s). V = Ve / √(σ) V: True Airspeed […]
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In flight mechanics, “lift during climb” refers to the aerodynamic force that opposes the weight of an aircraft while it is ascending vertically or at an upward angle. During climb, the aircraft is gaining altitude and increasing its potential energy, which requires an additional lift force to overcome gravity and maintain a positive rate of
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In flight mechanics and aviation, the “Flight Mach Number” is a dimensionless parameter used to express an aircraft’s speed relative to the speed of sound in the surrounding air. It is a critical parameter in high-speed flight and is denoted by the symbol “M.” The Flight Mach Number is defined as the ratio of the
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The surface pressure coefficient (Cp) is a dimensionless quantity used in fluid dynamics, especially in aerodynamics, to describe the pressure distribution over a body’s surface exposed to a fluid flow. It is commonly used to analyze and understand the aerodynamic forces acting on objects such as airfoils, wings, and other streamlined or bluff bodies. This
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Drag in climb refers to the aerodynamic force that acts opposite to the direction of motion of an aircraft while it is ascending vertically or at an upward angle (climbing). Drag is one of the aerodynamic forces that an aircraft must overcome during climb to maintain a positive rate of climb. D = (1/2) ρ
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The power required at the beginning of a flight refers to the amount of power that the aircraft’s engines or propulsion system must produce to overcome the aerodynamic drag and other resistive forces during takeoff and initial climb. Power required in the beginning of the flight =T*V/1000 T: Thrust. It is the force generated by
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In flight mechanics and aerodynamics, the “Lift Coefficient” (CL) is a dimensionless parameter that represents the lift force generated by an airfoil or wing relative to the dynamic pressure of the airflow. The lift coefficient is an essential concept in understanding the aerodynamics of flight and plays a significant role in aircraft design and performance
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In aerodynamics, the flow around a cylinder can be described using potential flow theory. The flow has two components: the uniform flow component (V∞) and the vortex flow component (Vθ) due to circulation (represented by Γ) around the cylinder. Vr is the radial component of velocity Vθ is the tangential component of velocity V∞ is
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In aerodynamics, uniform flow refers to a type of ideal flow pattern where the fluid velocity remains constant across a large region. In the case of two-dimensional flow (flow that occurs within a plane). The stream function (ψ) is a mathematical function used to describe the flow of an incompressible fluid (such as air) in
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Thermal conductivity (k) is a material property that measures how well a material conducts heat. It quantifies the ability of a substance to transfer thermal energy through conduction. In other words, it describes how easily heat flows through a material when there is a temperature gradient. k is the thermal conductivity μ is the molecular
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