Questions Archive - Page 27 of 38

At a given point on the surface of the wing of the airplane the flow velocity is \(130 \;m/s\). Calculate the pressure coefficient at this point.

An airplane flying at standard sea level has a velocity of \(98.8 \;m/s\). At a given point on the surface …

incompressible flow

Worldtech Asked on 1st November 2019 in Aerodynamics.

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A Pitot tube on an airplane flying at standard sea level reads \(1.07\times 10^{5}\; N/m^{2}\). What is the velocity of the airplane?

A Pitot tube on an airplane flying at standard sea level reads \(1.07\times 10^{5}\; N/m^{2}\). What is the velocity of …

incompressible flow

techAir Asked on 1st November 2019 in Aerodynamics.

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Consider a low-speed open-circuit subsonic wind tunnel with an inlet-to-throat area ratio of \(12\). The tunnel is turned on, and the pressure difference between the inlet (the settling chamber) and the test section is read as a height difference of \(10 \;cm\) on a U-tube mercury manometer. Calculate the velocity of the air in the test section.

Consider a low-speed open-circuit subsonic wind tunnel with an inlet-to-throat area ratio of \(12\). The tunnel is turned on, and …

incompressible flow

Worldtech Asked on 1st November 2019 in Aerodynamics.

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Consider a venturi with a small hole drilled in the side of the throat. This hole is connected via a tube to a closed reservoir. The purpose of the venturi is to create a vacuum in the reservoir when the venturi is placed in an airstream. Consider a venturi with a small hole drilled in the side of the throat. This hole is connected via a tube to a closed reservoir. The purpose of the venturi is to create a vacuum in the reservoir when the venturi is placed in an airstream.

Consider a venturi with a small hole drilled in the side of the throat. This hole is connected via a …

incompressible flow

techAir Asked on 31st October 2019 in Aerodynamics.

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Consider a venturi with a throat-to-inlet area ratio of 0.8, mounted on the side of an airplane fuselage. The airplane is in flight at standard sea level. If the static pressure at the throat is 2100 lb/ft^2, calculate the velocity of the airplane.

Consider a venturi with a throat-to-inlet area ratio of \(0.8\), mounted on the side of an airplane fuselage. The airplane …

incompressible flow

Worldtech Asked on 31st October 2019 in Aerodynamics.

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Consider an airfoil in a wind tunnel (i.e. a wing that spans the entire test section). Prove that the lift per unit span can be obtained from the pressure distributions on the top and bottom walls of the wind tunnel (i.e., from the pressure distributions on the walls above and below the airfoil).

Consider an airfoil in a wind tunnel (i.e., a wing that spans the entire test section). Prove that the lift …

fluids

techAir Asked on 31st October 2019 in Aerodynamics.

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Consider a body of arbitrary shape. If the pressure distribution over the surface of the body is constant, prove that the resultant pressure force on the body is zero.

Consider a body of arbitrary shape. If the pressure distribution over the surface of the body is constant, prove that …

fluids

Worldtech Asked on 31st October 2019 in Aerodynamics.

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Calculate the stream function and velocity potential.Using your results, show that lines of constant \( \phi\) are perpendicular to lines of constant \(\psi\).

Assuming the velocity field given as \(u = cx\) and \(v = −cy\), where \(c\) is a constant pertains to …

fluids

techAir Asked on 30th October 2019 in Aerodynamics.

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Consider a flow field in polar coordinates, where the stream function is given as \(ψ = ψ(r, θ)\). Starting with the concept of mass flow between two streamlines, derive Equations \(\rho V_{r}=\frac{1}{r}\frac{\partial \bar{\psi }}{\partial \theta}\) and \(\rho V_{\theta}=-\frac{\partial\bar{\psi} }{\partial r}\).

Consider a flow field in polar coordinates, where the stream function is given as \(ψ = ψ(r, θ)\). Starting with …

fluids

Worldtech Asked on 30th October 2019 in Aerodynamics.

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Consider a length of pipe bent into a U-shape. The inside diameter of the pipe is \(0.5\;m\). Air enters one leg of the pipe at a mean velocity of \(100\; m/s\) and exits the other leg at the same magnitude of velocity, but moving in the opposite direction. Calculate the magnitude and direction of the force exerted on the pipe by the airflow.

Consider a length of pipe bent into a U-shape. The inside diameter of the pipe is \(0.5\;m\). Air enters one …

fluids

techAir Asked on 29th October 2019 in Aerodynamics.

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