The Total Pressure Recovery Factor quantifies how well an intake system is able to recover the total pressure of the incoming air. A high total pressure recovery indicates a more efficient intake system, which is crucial for optimal engine performance. R is the Total Pressure Recovery Factor. Pt​ is the total pressure at the inlet. […]
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The Mach angle is a geometric angle that describes the angle between the direction of an object moving through a fluid (like an aircraft) and the Mach cone, which is a shock wave created by the object when it moves through the fluid at a speed greater than the speed of sound. θ is the
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The pitch angle of an aircraft refers to the angle at which the longitudinal axis of the aircraft deviates from the horizontal plane. It indicates whether the aircraft’s nose is pointing upwards (positive pitch) or downwards (negative pitch) relative to the horizontal. The pitch angle of an aircraft is also commonly known as the attitude
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The rate of climb is a performance parameter used in aircraft design and aviation to describe the vertical speed at which an aircraft can ascend. It is commonly denoted as ROC and is expressed in feet per minute (ft/min) or meters per second (m/s). T is the thrust generated by the aircraft’s engines, D is
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The Static Margin is a measure of the longitudinal stability of an aircraft. It represents the distance between the center of gravity  and the aerodynamic center  normalized by the mean aerodynamic chord SM is the static margin, Xcg​ is the location of the aircraft’s center of gravity, Xac​ is the location of the aerodynamic center,
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Potential energy is the energy an object possesses due to its position or state. In the context of aircraft design, potential energy is often associated with the aircraft’s altitude above a reference point, such as the Earth’s surface or a specified datum. PE is the potential energy, m is the mass of the object, g
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The glide ratio of an aircraft is defined as the ratio of the horizontal distance traveled to the vertical distance descended during a glide. The formula for calculating the glide ratio is: where: θ is the Glide angle, R is Glide ratio.
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Glide angle from aerodynamic ratio is an approximation of the angle between the horizontal plane and the trajectory of an aircraft during descent, derived from its lift-to-drag ratio, offering insight into its aerodynamic efficiency in gliding conditions. where: θ is the glide angle, L/D is the lift-to-drag ratio, L is the Lift force in N,
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Glide velocity refers to the horizontal speed of an aircraft during a descent without engine power, vital for determining horizontal travel distance in emergency scenarios. The formula to calculate Glide velocity as follows: where: W/S is the wing loading (kg/m2), θ is the Glide Angle in degrees CL is the Coefficient of Lift, V∞ is the
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Rocketry and aerospace engineering typically associate with the concept of the Burnout Velocity Calculator. This concept, by calculating the velocity of a rocket at the precise moment its propellant is completely consumed, essentially defines what we know as the Burnout Velocity. Where: Vburnout is the burnout velocity (final velocity). Vinitial is the initial velocity (velocity at
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