Wing loading Calculator in aviation, refers to the amount of weight supported by a given area of an aircraft’s wing. It is a critical parameter in aircraft design and performance, as it affects factors such as lift, drag, stall speed, and maneuverability. Wing loading Calculator is a crucial concept in aviation, representing the amount of […]
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Wing aspect ratio is a measure used in aerodynamics to describe the ratio of the wingspan of an aircraft to its average chord (the average distance between the leading and trailing edges of the wing). It is calculated by dividing the square of the wingspan by the wing area. Aspect ratio plays a significant role
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The formula for supersonic flow is complex and depends on various factors such as Mach number, specific heat ratio, temperature, and pressure ratios. To calculate supersonic flow properties, including Mach number, you may need to use equations specific to the particular scenario. Where: γ is the specific heat ratio, R is the specific gas constant,
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The formula for transonic flow is typically described using the Mach number, which represents the speed of an object relative to the speed of sound in the surrounding medium. Where: M = Mach number V = velocity of the object a = speed of sound in the medium
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Incompressible flow is a fluid flow in which the density of the fluid remains constant throughout the flow field. In other words, the flow is such that changes in pressure and temperature do not significantly alter the density of the fluid. Where: ˙m˙ is the mass flow rate (constant) ρ is the density of the
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A Mach cone, also known as a Mach shock wave or Mach angle, is a cone-shaped region of compressed air or gas that forms around an object moving through a fluid (such as air or water) at a speed greater than the speed of sound in that fluid. Where: θ is the angle of the
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The Prandtl-Glauert transformation, also known as the compressibility correction, is used to correct the lift and drag coefficients calculated for an incompressible flow to account for the effects of compressibility at high speeds. It’s expressed as: Where: CLα is the lift coefficient corrected for compressibility effects. CL0 is the lift coefficient at a specific
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The critical Mach number is the velocity at which the airflow over an object or airfoil reaches the speed of sound. It’s a significant parameter in aerodynamics because it marks the boundary between subsonic and supersonic flow regimes. Where: Mcr is the critical Mach number, γ is the specific heat ratio (ratio of specific heats),
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The formula for calculating flap deflection depends on various factors such as the type of flap, the aircraft’s configuration, and aerodynamic considerations. This formula relates the change in lift coefficient (due to flap deflection) to the change in flap angle.
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Lift augmentation refers to the increase in lift generated by an aircraft beyond its baseline or nominal lift characteristics. This increase in lift can be achieved through various means such as deploying flaps, slats, leading-edge devices, or other aerodynamic modifications. Where: ΔCL is the lift augmentation factor (dimensionless). S add-on is the added-on lifting surface
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