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Prove that the velocity potential and the stream function for a source flow, satisfy Laplace’s equation.
Prove that the velocity potential and the stream function for a source flow, satisfy Laplace’s equation.
incompressible flow

techAir Asked on 3rd November 2019 in Aerodynamics.
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Prove that the velocity potential and the stream function for a uniform flow , satisfy Laplace’s equation.
Prove that the velocity potential and the stream function for a uniform flow , satisfy Laplace’s equation.
incompressible flow

Worldtech Asked on 3rd November 2019 in Aerodynamics.
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Show that a source flow is a physically possible incompressible flow everywhere except at the origin. Also show that it is irrotational everywhere.
Show that a source flow is a physically possible incompressible flow everywhere except at the origin. Also show that it …
incompressible flow

Worldtech Asked on 2nd November 2019 in Aerodynamics.
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- 1 answers
- 0 votes
Consider a uniform flow with velocity \(V_{∞}\). Show that this flow is a physically possible incompressible flow and that it is irrotational.
Consider a uniform flow with velocity \(V_{∞}\). Show that this flow is a physically possible incompressible flow and that it …
incompressible flow

Worldtech Asked on 2nd November 2019 in Aerodynamics.
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- 1 answers
- 0 votes
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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- 1 answers
- 0 votes
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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- 1 answers
- 0 votes
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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- 1 answers
- 0 votes
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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- 1 answers
- 0 votes
An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively ( specific gas constant is 287 J/kg-K), find the circulation on the airfoil.
An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the …
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incompressible flow

Kisan Kumar Asked on 30th September 2019 in Aerodynamics.
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