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The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of \(600\,K\) and \(11\,atm\). If the flow …
- 34 views
- 1 answers
- 0 votes
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Find the enthalpy change, internal energy change and entropy change across a shock wave whose upstream air temperature and pressure …
- 49 views
- 1 answers
- 0 votes
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Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of \(4.441\). …
- 40 views
- 1 answers
- 0 votes
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A flow is passing over a \({20^ \circ }\) half-angle wedge having a upstream Mach number, pressure and temperature of …
- 58 views
- 1 answers
- 0 votes
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An oblique shock wave is generated with a wave angle of \({30^ \circ }\) in a Mach \(4\) flow, at …
- 57 views
- 1 answers
- 0 votes
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Find the neutral point and static margin of an airplane if the location of the aerodynamic center is at \( …
- 81 views
- 1 answers
- 0 votes
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Consider wing- body combination of an airplane. Find the coefficient of lift of this wing body if the coefficient of …
- 64 views
- 1 answers
- 0 votes
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Find the turn radius and turn rate of an airplane, flying at a velocity of \(403.2\, km/h\) and has a …
- 72 views
- 1 answers
- 0 votes
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Find the gliding distance of an aircraft flying at an altitude of \(1500\,m\) with a maximum lift to drag ratio …
- 67 views
- 1 answers
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Find the stalling speed of an airplane which has a wing area of \(17\,m^2\) and is flying at sea level …
- 61 views
- 1 answers
- 0 votes
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Find the magnitude of velocity at point \((2,3)\) for a two-dimensional flow field whose stream function is given by \(\psi = 2x^{2}-y^{2}\).
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Find the circulation around a closed contour which is defined by \(x = 1, y = 0, y = 1\) and \( x = 0\).
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Find the vorticity.
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Find the equation of the streamline which is passing through the point \(\left ( 2,6 \right )\).
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Find the nozzle's exit temperature and density if its exit pressure is \(1\,atm\).
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