Aerodynamics Archives - Page 7 of 12

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.

3K views
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.

3K views
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.

1K views
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.

865 views
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.

2K views
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.

1K views
1 answers
0 votes

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.

1K views
1 answers
0 votes

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.

3K views
1 answers
0 votes

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.

1K views
1 answers
0 votes

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.

5K views
1 answers
0 votes

Tags

LATEST QUESTIONS

Tags