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An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of …
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- 1 answers
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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 …
- 105 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 …
- 144 views
- 1 answers
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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 \(4.441\). …
- 91 views
- 1 answers
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A flow is passing over a \({20^ \circ }\) half-angle wedge having a upstream Mach number, pressure and temperature of …
- 112 views
- 1 answers
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An oblique shock wave is generated with a wave angle of \({30^ \circ }\) in a Mach \(4\) flow, at …
- 110 views
- 1 answers
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Find the neutral point and static margin of an airplane if the location of the aerodynamic center is at \( …
- 136 views
- 1 answers
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Consider wing- body combination of an airplane. Find the coefficient of lift of this wing body if the coefficient of …
- 98 views
- 1 answers
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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 …
- 126 views
- 1 answers
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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 …
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- 0 votes
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Question Tag: Airplane design
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LATEST QUESTIONS
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Find the location of the aerodynamic center.
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Find the angle of attack for this airfoil, if the lift per unit span produced is \(1400\,N\).
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Can an airfoil fly upside-down ?
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Find the circulation around a spinning circular cylinder in free stream flow of velocity \(40\,m/s\) at a standard sea level conditions, if the lift produced by the cylinder is \(8\,N/m\) of span.
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An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of the wing where the flow velocity is \(140\,m/s\).
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