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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.
- 1K 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.
- 1K views
- 1 answers
- 0 votes
Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $8^{\circ}$ in a Mach $3$ flow.
Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $8^{\circ}$ …
drag coefficient

lift and drag

lift coefficient

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 26th March 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
The upstream Mach number, pressure and temperature of a supersonic flow over an expansion corner having deflection angle $\theta =25^{^{\circ}}$ is $M_{1}=2.2,\,p_{1}=0.8\,atm$ and $T_{1}=360\,K$ . Find the downstream Mach number, pressure, temperature, density , total pressure, total temperature, and the angles made by the forward and rearward Mach lines with local flow direction.
The upstream Mach number, pressure and temperature of a supersonic flow over an expansion corner having deflection angle $\theta =25^{^{\circ}}$ …
airspeed

Expansion wave

Shock waves

Worldtech Asked on 26th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
An oblique shock wave is generated at a compression corner having a deflection angle of $20^{^{\circ}}$ . The oblique shock wave is reflected from a straight horizontal wall which is present above the compression corner. The upstream flow properties are $M_{1}=3.4,\,p_{1}=1\,atm,\,T_{1}=300\,K$ . Find the Mach number, pressure and temperature behind the reflected shock wave and angle made by the reflected shock wave with the upper wall.
An oblique shock wave is generated at a compression corner having a deflection angle of $20^{^{\circ}}$ . The oblique shock wave …
airspeed

oblique shock waves

Shock waves

Supersonic airplanes

techAir Asked on 26th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
A flow is passing over a ${20^ \circ }$ half-angle wedge having a upstream Mach number, pressure and temperature of $2.8,\,1\,atm\,$ and $310\,K$ . Find the wave angle and downstream Mach number, pressure and temperature.
A flow is passing over a ${20^ \circ }$ half-angle wedge having a upstream Mach number, pressure and temperature of …
Airplane design

airspeed

Mach number

Shock waves

Kumar59 Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Find the pressure, temperature , Mach number, total pressure and total temperature behind the oblique shock wave.
An oblique shock wave is generated with a wave angle of ${30^ \circ }$ in a Mach $4$ flow, at …
Airplane design

airspeed

Shock waves

Supersonic flow

Worldtech Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes

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