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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

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Shock waves

Supersonic flow

Worldtech Asked on 15th April 2021 in Aerodynamics.
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- 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 $\theta =25^{^{\circ}}$ …
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Expansion wave

Shock waves

Worldtech Asked on 26th March 2021 in Aerodynamics.
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- 1 answers
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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 …
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oblique shock waves

Shock waves

Supersonic airplanes

techAir Asked on 26th March 2021 in Aerodynamics.
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- 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

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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

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Shock waves

Supersonic flow

Worldtech Asked on 11th March 2021 in Aerodynamics.
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- 1 answers
- 0 votes
Find the upstream Mach number if there is a entropy increase across the normal shock wave of $220\,J/\left( {kg.K} \right)$ .
Find the upstream Mach number if there is an entropy increase across the normal shock wave of $220\,J/\left( {kg.K} \right)$ .
Mach number

normal shock waves

Shock waves

thermodynamics

techAir Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
A flow passes through a normal shock wave has a pressure, temperature and Mach number of $1\,atm,\,295\,K$ and $2.8$ upstream of the shock wave. Find ${P_2},{T_2},\,{\rho _2},\,{M_2},{P_{02}}$ and ${T_{02}}$ downstream of the shock wave.
A flow passes through a normal shock wave has a pressure, temperature and Mach number of $1\,atm,\,295\,K$ and $2.8$ upstream …
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normal shock waves

Shock waves

Supersonic flow

Kumar59 Asked on 11th March 2021 in Aerodynamics.
- 954 views
- 1 answers
- 0 votes
What are shock waves? How does it originates?
What are shock waves? How does it originates?
Shock waves

Supersonic airplanes

Supersonic flow

Kisan Kumar Asked on 18th January 2021 in Aerodynamics.
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- 1 answers
- 0 votes
Calculate the wave drag on the wings of an airplane which is flying at a Mach number of $2.1$ at an altitude of $10000\, m$ . The airplane weights $70000\, N$ and has a wing area of $20\, m^2$ .
Calculate the wave drag on the wings of an airplane which is flying at a Mach number of $2.1$ at …
drag

drag force

Shock waves

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 18th January 2021 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes

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