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The x and y components of a velocity field are given by u = 5y/(x^2 + y^2) and v = (-5x/(x^2 + y^2). Calculate the circulation around a circular path of radius 3m. Let the units of u and v be in m/s.
Consider a velocity field where x and y components of velocity are \(u = 5y/\left( {{x^2} + {y^2}} \right)\) and \(v = …
Circulation

techAir Asked on 2nd January 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
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 …
incompressible flow

techAir Asked on 2nd January 2019 in Aerodynamics.
- 1K 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 …
techAir Asked on 1st January 2019 in Aerodynamics.
- 982 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 …
incompressible flow

techAir Asked on 1st January 2019 in Aerodynamics.
- 1K 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 …
techAir Asked on 1st January 2019 in Aerodynamics.
- 989 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 …
incompressible flow

irrotational flow

techAir Asked on 31st December 2018 in Aerodynamics.
- 2K 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.
incompressible flow

irrotational flow

techAir Asked on 31st December 2018 in Aerodynamics.
- 1K 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.
Laplace's equation

techAir Asked on 31st December 2018 in Aerodynamics.
- 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 …
Worldtech Asked on 30th December 2018 in Aerodynamics.
- 2K 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, …
Worldtech Asked on 30th December 2018 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes

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