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• ## Calculate the location of center of pressure of an airfoil section at an angle of attack of 5o, whose coefficient of lift, cl is 0.80 and cm,c/4 is -0.08. Consider incompressible flow over the airfoil.

Calculate the location of center of pressure of an airfoil section at an angle of attack of $${{\rm{5}}^{\rm{o}}}$$, whose coefficient of …

Asked on 2nd January 2019 in
• 896 views
• 1 answers
• 0 votes
• ## Water is flowing through a pipe, having inlet inside diameter of 80 mm at 8m/sec. Calculate the velocity at exit  if inside diameter is reduced to 30 mm.

Water is flowing through a pipe, having inlet inside diameter of 80 mm at 8 m/sec. Calculate the velocity at …

Asked on 2nd January 2019 in
• 599 views
• 1 answers
• 0 votes
• ## At a given point on the surface of wing flow velocity is 150 m/sec. What is the pressure coefficient at this point? The velocity of an aircraft is 100 m/sec.

The velocity of an aircraft is 100 m/sec. At a given point on the surface of wing flow velocity is …

Asked on 1st January 2019 in
• 662 views
• 1 answers
• 0 votes
• ## Pressure coefficient at a certain point on an airfoil is -4.2.Calculate velocity at this point assuming the flow over the airfoil to be inviscid and incompressible.

Pressure coefficient at a certain point on an airfoil is -4.2.Calculate velocity at this point assuming the flow over the …

Asked on 1st January 2019 in
• 802 views
• 1 answers
• 0 votes
• ## Find pressure coefficient at a point on an  airfoil where velocity is 220 ft/s, which is in a free stream flow of 100 ft/s.

Find pressure coefficient at a point on an  airfoil where velocity is 220 ft/s, which is in a free stream …

Asked on 1st January 2019 in
• 678 views
• 1 answers
• 0 votes
• ## For a source flow, show that it is a physically possible incompressible flow except at origin. Also, show that it is irrotational.

For a source flow, show that it is a physically possible incompressible flow except at origin. Also, show that it …

Asked on 31st December 2018 in
• 1K views
• 1 answers
• 0 votes
• ## Show that a uniform flow with velocity $${V_\infty }$$ is a physically possible incompressible flow and is irrotational.

Show that a uniform flow with velocity $${V_\infty }$$ is a physically possible incompressible flow and is irrotational.

Asked on 31st December 2018 in
• 994 views
• 1 answers
• 0 votes
• ## Prove that velocity potential and stream function for a uniform flow and source flow satisfies Laplace’s equation.

Prove that velocity potential and stream function for a uniform flow and source flow satisfies Laplace’s equation.

Asked on 31st December 2018 in
• 2K views
• 1 answers
• 0 votes
• ## Consider the lifting flow over a circular cylinder of a given radius and with a given circulation. If velocity is doubled does the shape of streamlines change.

If the velocity $${V_\infty }$$ of a flow is doubled in the case of lifting flow over a circular cylinder of …

Asked on 30th December 2018 in
• 1K views
• 1 answers
• 0 votes
• ## Consider the lifting flow over a circular cylinder with a diameter of 0.8m. Calculate the lift per unit span, considering freestream sea level conditions.

Calculate the lift per unit span for a lifting flow over a circular cylinder with a diameter of 0.8 m, …

Asked on 30th December 2018 in
• 1K views
• 1 answers
• 0 votes