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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.
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What are expansion waves?
What are expansion waves? How does it originates?
Expansion wave

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 18th January 2021 in Aerodynamics.
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- 1 answers
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Consider a two-dimensional duct with a straight horizontal lower wall, and a straight upper wall inclined upward through the angle 3 degree. Calculate the average flow Mach number over AB, assuming that M varies linearly along that portion of AB inside the expansion wave.
Calculate the average flow Mach number over AB, assuming that M varies linearly along portion AB inside the expansion wave.The …
Compressible flow

Expansion wave

techAir Asked on 4th July 2019 in Aerodynamics.
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- 1 answers
- 0 votes