1. The lift on a spinning circular cylinder in a freestream with a velocity of 33.5...
1. The lift on a spinning circular cylinder in a freestream with a velocity of 33.5 m/s and at standard sea level conditions is 6.3 N/m of span. Calculate the circulation around the cylinder. Enter your answer to two decimal places in units of m 2 /s.
2. In the given figure of flow over a cylinder, where is a
stagnation point located?
|
(R, pi/4) |
||
|
(R, pi/2) |
||
|
(R, pi) |
||
|
(R, 3*pi/2) |
Homework Answers
In 2nd question diagram is not given. Please update it's diagram.
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1. The lift on a spinning circular cylinder in a freestream with
a velocity of 33.5...
3. (4 pts) Write down the velocity potential for a lifting circular cylinder in a uniform...
3. (4 pts) Write down the velocity potential for a lifting circular cylinder in a uniform flow of velocity V. Find the velocity components in this flow field. For what value of the circulation will the stagnation point be located on the surface of the cylinder at: (a) (r, 8) = (RO), (b) (r,®) = (R, -*/2).
Air flow over a cylinder of radius R- 150mm is modelled as a steady, frictionless and incompressible flow. The vector form of the velocity field is 1" The freestream velocity far away from the cy...
Air flow over a cylinder of radius R- 150mm is modelled as a steady, frictionless and incompressible flow. The vector form of the velocity field is 1" The freestream velocity far away from the cylinder is 75m/s and the static pressure is 101.3kPa. Note that this is similar to worked example 5.1 done during the lecture. However, now you know the Bernoulli equation can be used along a streamline...so: Find a) The stagnation pressure at the leading edge of the...
use a Reynolds number of 2.6x10^5 to find using graphs 2. Consider an NACA 23015 airfoil...
use a Reynolds number of 2.6x10^5 to find using
graphs
2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24...
UML each) For the next two questions: The velocity potential of a cylinder of radius a...
UML each) For the next two questions: The velocity potential of a cylinder of radius a a given by: a cylinder of radius a and with circulation is The uniform flow is U circulation is l = 3 m = 10 m/s, the radius of the cylinder is a = 2.5 m, an /s. The density of the flow of is 1 kg/m. te cylinder is a = 2.5 m, and the strength of the 19. The subsequent lift force...
A sphere and a circular cylinder (with its axis perpendicular to the flow) are mounted in the sam...
A sphere and a circular cylinder (with its axis perpendicular to the flow) are mounted in the same freestream. A pressure tap exists at the top of the sphere, and this is connected via a tube to one side of a manometer. The other side of the manometer is connected to a pressure tap on the surface of the cylinder. This tap is located on the cylindrical surface such that the deflection of the fluid in the manometer indicates that...
Consider an NACA 2305 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64...
Consider an NACA 2305 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) 3.
Problem 3: ter with density #1000k/m3 is flowing around a cylinder submergedinto a river. The riv...
Problem 3: ter with density #1000k/m3 is flowing around a cylinder submergedinto a river. The river velocity is given by U-5 m/s and the cylinder radius is R -1.5 m. Calculate the pressure difference between point So (stagnation point) and the point S located at 45° on the surface. Note that as per the inviscid potential flow theory, the velocity at the external surface of the cylinder is given by v,--2U sin . Use g 9.81 m/s2 for gravity U...
2. (30 points) The figure below shows the streamlines for the flow past a spinning circular cylin...
2. (30 points) The figure below shows the streamlines for the flow past a spinning circular cylinder. In the cylindrical coordinates, the stream function can be written as นุ่ Uosine- Kin (), where R is the radius of the cylinder. Assuming that the pressure in the far upstream is po, find the pressure distribution on the surface.
2. (30 points) The figure below shows the streamlines for the flow past a spinning circular cylinder. In the cylindrical coordinates, the stream...
Consider a circular cylinder of radius a whose central axis is stationary. The cylinder is surrounded by a fluid that i...
Consider a circular cylinder of radius a whose central axis is stationary. The cylinder is surrounded by a fluid that is moving with a uniform steady velocity Uk far from the cylinder; the cylinder axis is in the z-direction The cylinder is also spinning on its axis with constant angular velocity, Ω2, where x, у and z are the usual Cartesian unit vectors We wish to model this 2D flow using an inviscid approximation. This is achieved by first calculating...
ME420 Intermediate Fluid Mechanics Name B. Long answer questions (20 points each). 1. The figure below shows the streamlines for the flow past a spinning circular cylinder. In the cylindrical coo...
ME420 Intermediate Fluid Mechanics Name B. Long answer questions (20 points each). 1. The figure below shows the streamlines for the flow past a spinning circular cylinder. In the cylindrical coordinates, the stream function can be written as ψ Uosine (r-7/-Kln (5). where R is the radius of the cylinder. Assuming that the pressure in the far upstream is po. find the pressure distribution on the surface.
ME420 Intermediate Fluid Mechanics Name B. Long answer questions (20 points each). 1....
3. (4 pts) Write down the velocity potential for a lifting circular cylinder in a uniform flow of velocity V. Find the velocity components in this flow field. For what value of the circulation will the stagnation point be located on the surface of the cylinder at: (a) (r, 8) = (RO), (b) (r,®) = (R, -*/2).
Air flow over a cylinder of radius R- 150mm is modelled as a steady, frictionless and incompressible flow. The vector form of the velocity field is 1" The freestream velocity far away from the cylinder is 75m/s and the static pressure is 101.3kPa. Note that this is similar to worked example 5.1 done during the lecture. However, now you know the Bernoulli equation can be used along a streamline...so: Find a) The stagnation pressure at the leading edge of the...
use a Reynolds number of 2.6x10^5 to find using
graphs
2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24...
UML each) For the next two questions: The velocity potential of a cylinder of radius a a given by: a cylinder of radius a and with circulation is The uniform flow is U circulation is l = 3 m = 10 m/s, the radius of the cylinder is a = 2.5 m, an /s. The density of the flow of is 1 kg/m. te cylinder is a = 2.5 m, and the strength of the 19. The subsequent lift force...
Consider an NACA 2305 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) 3.
Problem 3: ter with density #1000k/m3 is flowing around a cylinder submergedinto a river. The river velocity is given by U-5 m/s and the cylinder radius is R -1.5 m. Calculate the pressure difference between point So (stagnation point) and the point S located at 45° on the surface. Note that as per the inviscid potential flow theory, the velocity at the external surface of the cylinder is given by v,--2U sin . Use g 9.81 m/s2 for gravity U...
2. (30 points) The figure below shows the streamlines for the flow past a spinning circular cylinder. In the cylindrical coordinates, the stream function can be written as นุ่ Uosine- Kin (), where R is the radius of the cylinder. Assuming that the pressure in the far upstream is po, find the pressure distribution on the surface.
2. (30 points) The figure below shows the streamlines for the flow past a spinning circular cylinder. In the cylindrical coordinates, the stream...
Consider a circular cylinder of radius a whose central axis is stationary. The cylinder is surrounded by a fluid that is moving with a uniform steady velocity Uk far from the cylinder; the cylinder axis is in the z-direction The cylinder is also spinning on its axis with constant angular velocity, Ω2, where x, у and z are the usual Cartesian unit vectors We wish to model this 2D flow using an inviscid approximation. This is achieved by first calculating...
ME420 Intermediate Fluid Mechanics Name B. Long answer questions (20 points each). 1. The figure below shows the streamlines for the flow past a spinning circular cylinder. In the cylindrical coordinates, the stream function can be written as ψ Uosine (r-7/-Kln (5). where R is the radius of the cylinder. Assuming that the pressure in the far upstream is po. find the pressure distribution on the surface.
ME420 Intermediate Fluid Mechanics Name B. Long answer questions (20 points each). 1....
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