– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. In boundary layer theory, this equation is crucial for determining the shear stress exerted on a surface submerged in a fluid flow. It plays a pivotal role in calculating skin-friction drag, a significant component of the total aerodynamic drag that a body encounters while moving […]
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– D. Raymer – Aircraft Design. A Conceptual Approach (1992) Wf​: Weight of the fuel required for the mission. Wo​: Initial takeoff weight of the aircraft. Wx​: Weight of the aircraft after completing the mission (excluding fuel weight). The factor 1.06 accounts for a typical 6% reserve and trapped fuel allowance.
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The Coefficient of Lift for Max Glide Endurance is a parameter that signifies the lift efficiency required for achieving the longest possible duration of unpowered flight. It represents the ratio of the lift force generated by the aircraft’s wings to the dynamic pressure of the surrounding air and the wing’s area. In the context of
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Axial deformation is calculated using Hooke’s Law, which relates stress (σ) to strain (ε) for elastic deformation. The formula for axial deformation is given by: ​ where: δaxial​ = Axial deformation (in meters, m) F = Applied axial force or load (in newtons, N) L = Original length of the structural member (in meters, m)
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The cross-sectional area (A) represents the area enclosed by the shape of the structural member, typically perpendicular to the axis of bending or rotation. The SI units for the radius of gyration formula are meters (m) for length measurements (both r and any dimensions involved in calculating I and A). It’s essential to ensure that
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The radius of gyration (r) is a measure of how the mass or area of a structural member is distributed relative to its centroid or axis of rotation. It is commonly used in structural engineering to characterize the bending behavior of columns and beams For structural purposes, the radius of gyration is calculated based on
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The slenderness ratio (λ) is a dimensionless parameter used in structural engineering to evaluate the stability of slender columns under compressive loads. It is calculated based on the column’s effective length (Le​) and its radius of gyration (r). ​​ where: λ = Slenderness ratio (dimensionless) Le​ = Effective length of the column (in meters, m)
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Thermal strain refers to the deformation or change in dimensions of a material due to a change in temperature. It is calculated based on the material’s coefficient of thermal expansion (α) and the change in temperature (ΔT). Thermal strain is calculated using the formula: where: εthermal​ = Thermal strain (dimensionless) α = Coefficient of thermal
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Thermal stress refers to the stress that develops in a material due to a change in temperature. When a material is subjected to non-uniform temperature changes, different parts of the material expand or contract at different rates, leading to internal stresses. Thermal stress is calculated using the formula: where: σthermal​ = Thermal stress (in pascals,
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The percent reduction in area measures the decrease in cross-sectional area of a tensile specimen at the point of fracture compared to its original cross-sectional area. It is calculated using the formula: where: Ai​ is the initial cross-sectional area of the specimen (in square meters, m²). Af​ is the final cross-sectional area of the specimen
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