Boost your aerodynamic endeavors with the online aerodynamics calculator by ToDo Calculator. Tailored for aerospace engineers, researchers, and enthusiasts, this versatile tool facilitates a myriad of aerodynamics calculations. Leveraging the robust capabilities of ToDo Calculator, it delivers precise solutions across various parameters, from airfoil analysis to lift and moment calculations. With its intuitive interface, this calculator demystifies complex aerodynamic computations, empowering both professionals and students alike. Whether you’re crafting aircraft or delving into fluid dynamics, this resource accelerates your aerodynamics analysis, ensuring optimal performance in aerospace projects.
– 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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Capillary pressure refers to the pressure difference across the interface between two immiscible fluids in a capillary tube or porous medium Pc​ is the capillary pressure, γ is the surface tension of the liquid, θ is the contact angle between the liquid and the solid surface, r is the radius of the capillary.
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The Yawing Moment  is the moment about the vertical axis of an aircraft Cn​ is the yawing moment coefficient. β is the sideslip angle.
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The Lift Curve Slope (a) is a key parameter in aerodynamics that describes the rate at which the lift coefficient (CL​) changes with the angle of attack (α) for a wing. a is the lift curve slope. ΔCL​ is the change in lift coefficient. Δα is the change in angle of attack
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The Flow Mach Number (M) is a dimensionless parameter used to characterize the speed of an object moving through a fluid, particularly in the context of compressible flow like in aerodynamics M is the Flow Mach Number. V is the velocity of the object. a is the local speed of sound in the fluid.
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The Engine Thrust Deduction Factor represents the fraction of the engine thrust that is not available for accelerating the aircraft, as it is offset by the aerodynamic drag. E is the Engine Thrust Deduction Factor. T is the thrust produced by the engines. D is the total aerodynamic drag acting on the aircraft. W
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The thrust for a propeller-driven aircraft represents the relationship between the thrust produced by the propeller, the shaft power provided to the propeller, and the velocity of the aircraft. T: Thrust Pshaft​: Shaft power V: Velocity
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Specific Excess Power (excessPexcess​) is a measure of the surplus power available to an aircraft in climbing flight. P excess​ is the Specific Excess Power, T is the thrust produced by the aircraft’s engines, D is the total drag acting on the aircraft
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The lift coefficient (CL​) for an airfoil section is a critical parameter in aircraft design, representing the effectiveness of the airfoil in generating lift CL section​​ is the lift coefficient for the airfoil section. α is the angle of attack αL0​​ is the zero-lift angle of attack. 2π represents the lift-curve slope
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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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