• Question Tag: Compressible flow
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• Velocity potential of a subsonic compressible flow is $\phi(x,y) = V_{\infty}x + \frac{5}{\sqrt{1 – M_{\infty}^{2}}}e^{-2\pi\sqrt{1-M_{\infty}^{2}}y}sin2\pi x$ Freestream velocity, pressure and temperature are $$200\,m/s$$, $$1\,atm$$ and $$300\,K$$. Find the velocity, pressure and temperature at, $$(0.07\,m, 0.07\,m)$$.

Velocity potential of a subsonic compressible flow is $\phi(x,y) = V_{\infty}x + \frac{5}{\sqrt{1 – M_{\infty}^{2}}}e^{-2\pi\sqrt{1-M_{\infty}^{2}}y}sin2\pi x$ Freestream velocity, pressure and …

Kumar59 Asked on 13th January 2022 in
• 559 views
• An airfoil is in airflow with $$0.52$$ free stream Mach number. Local Mach number at a given point is $$0.82$$. Find the pressure coefficient at this point.

An airfoil is in airflow with $$0.52$$ free stream Mach number. Local Mach number at a given point is $$0.82$$. …

Worldtech Asked on 13th January 2022 in
• 583 views
• 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 …

techAir Asked on 4th July 2019 in
• 854 views