The downwash angle (δ) is the angle at which the wake of an aircraft descends due to the influence of the aircraft’s wing V is the induced velocity in the downward direction U is the freestream velocity.
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Volume fraction of matrix is a Proportion of composite volume occupied by matrix material. The formula is given by: Where: Vm​ is the volume fraction of the matrix. Vf​ is the volume fraction of the reinforcement.
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The critical angle of attack is the angle of attack at which an airfoil or wing experiences a stall. A stall occurs when the airflow over the wing separates, leading to a sudden decrease in lift. αcrit​ is the critical angle of attack, CLmax​​ is the maximum coefficient of lift, π is a mathematical
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Specific energy consumption refers to the amount of energy used per unit of a specific activity or output. Typically, industries, transportation, and building operations commonly use this metric to assess energy efficiency. Where: SEC is the specific energy consumption (e.g., kWh/kg, kWh/ton) The total energy consumed (e.g., in kilowatt-hours, kWh) constitutes E. Q is the
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Thrust Specific Fuel Consumption (TSFC) is a crucial parameter in aircraft design and is defined as the fuel consumption rate per unit of thrust produced by a jet engine TSFC is the thrust-specific fuel consumption, m˙fuel​ is the fuel mass flow rate, T is the thrust.
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The volume of a constituent Vi divided by the volume of all constituents of the mixture V prior to mixing. The formula is given by: Where: Vf​ is the volume fraction of reinforcement. Vreinforcement​ is the volume of the reinforcement material. Vtotal​ is the total volume of the composite material (including both the matrix material
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The trim lift coefficient (CLtrim​​) is the lift coefficient at which an aircraft is in a balanced or trimmed condition during level flight, meaning there is no net pitching moment and the aircraft remains stable without requiring continuous control inputs from the pilot to maintain its attitude. When an aircraft is in trim, the lift
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Thermal stress analysis involves calculating the stresses induced in a material due to changes in temperature. The formula is given by: Where: σ is the thermal stress (in units of pressure, typically expressed in Pascals or psi). E is the Young’s modulus or elastic modulus of the material (in units of pressure, typically expressed in
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Normal stress, often denoted by the symbol σ (sigma), is a measure of the force acting perpendicular to the cross-sectional area of a material. σ (sigma) is the normal stress, F is the force acting perpendicular to the surface, A is the cross-sectional area.
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The critical Mach number is the speed at which airflow over an aircraft’s wing reaches the speed of sound. It marks the boundary between subsonic and transonic flow regimes. Exceeding this critical speed can lead to aerodynamic instabilities and performance issues. It’s a crucial parameter in aircraft design, helping engineers ensure safe and efficient flight
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