
Calculate the location of center of pressure of an airfoil section at an angle of attack of \({{\rm{5}}^{\rm{o}}}\), whose coefficient of …
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Water is flowing through a pipe, having inlet inside diameter of 80 mm at 8 m/sec. Calculate the velocity at …
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The velocity of an aircraft is 100 m/sec. At a given point on the surface of wing flow velocity is …
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Pressure coefficient at a certain point on an airfoil is 4.2.Calculate velocity at this point assuming the flow over the …
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Find pressure coefficient at a point on an airfoil where velocity is 220 ft/s, which is in a free stream …
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For a source flow, show that it is a physically possible incompressible flow except at origin. Also, show that it …
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Show that a uniform flow with velocity \({V_\infty }\) is a physically possible incompressible flow and is irrotational.
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Prove that velocity potential and stream function for a uniform flow and source flow satisfies Laplace’s equation.
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If the velocity \({V_\infty }\) of a flow is doubled in the case of lifting flow over a circular cylinder of …
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Calculate the lift per unit span for a lifting flow over a circular cylinder with a diameter of 0.8 m, …
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