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A velocity field is given by \(V=3yt\hat{i}+5x\hat{j}\). Find the equation of the streamline passing through the point \((5,3)\) at \(t =3\). Units of \(x,y\) are in meters and time-\(t\) is in seconds.
A velocity field is given by \(V=3yt\hat{i}+5x\hat{j}\). Find the equation of the streamline passing through the point \((5,3)\) at \(t …
fluids

streamlines

Kumar59 Asked on 5th May 2021 in Fluid mechanics.
- 1K views
- 1 answers
- 0 votes
Find the acceleration of a fluid particle in the \(x\) direction at \((x,y) = (3,1)\) for a velocity field, which is given by\(\vec{V} = 3y\hat{i}+4x\hat{j}\). \(x\) and \(y\) are in meters.
Find the acceleration of a fluid particle in the \(x\) direction at \((x,y) = (3,1)\) for a velocity field, which …
fluids

Kisan Kumar Asked on 5th May 2021 in Fluid mechanics.
- 1K views
- 1 answers
- 0 votes
Find the magnitude of velocity at point \((2,3)\) for a two-dimensional flow field whose stream function is given by \(\psi = 2x^{2}-y^{2}\).
Find the magnitude of velocity at point \((2,3)\) for a two-dimensional flow field whose stream function is given by \(\psi …
fluids

stream functions

streamlines

Worldtech Asked on 5th May 2021 in Fluid mechanics.
- 1K views
- 1 answers
- 0 votes
A velocity field is given by \(u=x^{2} + y\) and \(v= x^{3} + 2y\). Find the circulation around a closed contour which is defined by \(x = 1, y = 0, y = 1\) and \( x = 0\). Units of \(u\) and \(v\) are in \(m/s\).
A velocity field is given by \(u=x^{2} + y\) and \(v= x^{3} + 2y\). Find the circulation around a closed …
Circulation

techAir Asked on 15th April 2021 in Fluid dynamics.
- 1K views
- 1 answers
- 0 votes
A velocity field is given by \(u=\frac{y}{x^{3}+y^{3}}\) and \(v=\frac{-x}{x^{3}+y^{3}}\). Find its vorticity.
A velocity field is given by \(u=\frac{y}{x^{3}+y^{3}}\) and \(v=\frac{-x}{x^{3}+y^{3}}\). Find its vorticity.
Vorticity

Kumar59 Asked on 15th April 2021 in Fluid dynamics.
- 1K views
- 1 answers
- 0 votes
A velocity field is given by \(u=\frac{y}{x^{3}+y}\) and \(v=\frac{-x}{x^{3}+y}\). Find the equation of the streamline which is passing through the point \(\left ( 2,6 \right )\).
A velocity field is given by \(u=\frac{y}{x^{3}+y}\) and \(v=\frac{-x}{x^{3}+y}\). Find the equation of the streamline which is passing through the …
streamlines

Kisan Kumar Asked on 15th April 2021 in Fluid dynamics.
- 1K views
- 1 answers
- 0 votes
The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of \(600\,K\) and \(11\,atm\). If the flow is isentropic through the nozzle of this wind tunnel, find the nozzle’s exit temperature and density if its exit pressure is \(1\,atm\).
The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of \(600\,K\) and \(11\,atm\). If the flow …
Aircraft performance

Airplane design

Supersonic airplanes

Supersonic flow

techAir Asked on 15th April 2021 in Aerodynamics.
- 967 views
- 1 answers
- 0 votes
Find the enthalpy change, internal energy change and entropy change across a shock wave.
Find the enthalpy change, internal energy change and entropy change across a shock wave whose upstream air temperature and pressure …
Aircraft performance

Airplane design

airspeed

Shock waves

Supersonic flow

Worldtech Asked on 15th April 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Find the combustion chamber pressure of a rocket engine using hydrogen and oxygen as propellants, whose mass flow in combustion chamber is \(300\,kg/s\). The temperature of the combustion chamber is \(3500\,K\). Gas flowing into the engine has a ratio of specific heats of \(1.2\) and a molecular weight of \(16\). The rocket nozzle throat area is \(0.25\,m^{2}\).
Find the combustion chamber pressure of a rocket engine using hydrogen and oxygen as propellants, whose mass flow in combustion …
rocket engine

rocket propulsion

techAir Asked on 26th March 2021 in Rocket and Space propulsion.
- 1K views
- 1 answers
- 0 votes
Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of \(4.441\). The test section pressure measured by a pitot tube is \(1.5\, atm\).
Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of \(4.441\). …
Airplane design

airspeed

Supersonic flow

Kisan Kumar Asked on 26th March 2021 in Design.
- 996 views
- 1 answers
- 0 votes

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