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Write a Matlab code for a doublet at the origin.
Write a Matlab code for a doublet at the origin.
incompressible flow

Matlab

techAir Asked on 5th September 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Write a matlab code for a Uniform flow flowing in X direction.
Write a matlab code for a uniform flow flowing in X – direction having a constant velocity depicting equipotential lines …
incompressible flow

Worldtech Asked on 10th August 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Write a matlab code for a source at the origin.
Write a MATLAB code for a source flow at the origin.
incompressible flow

techAir Asked on 10th August 2019 in Aerodynamics.
- 1K views
- 0 answers
- 0 votes
Write a matlab code for vortex panel method.
Write a matlab code for vortex panel method.
incompressible flow

vortex flow

techAir Asked on 3rd August 2019 in Aerodynamics.
- 1K views
- 0 answers
- 0 votes
The Kutta-Joukowski theorem \({L}’=\rho _{\infty}V_{\infty}\tau\) was derived exactly for the case of the lifting cylinder. Implement a physical argument for this theorem.
Apply Kutta-joukowski theorem for a two dimensional body of arbitrary shape by making a physical argument.
incompressible flow

Worldtech Asked on 2nd July 2019 in Aerodynamics.
- 1K 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
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
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
In an inviscid, incompressible flow of air along a streamline, the air density is 0.002377 slug/ft^3. Find the pressure at a point.
In an inviscid, incompressible flow of air along a streamline, the air density is 0.002377 \({\rm{slug/f}}{{\rm{t}}^{\rm{3}}}\). At a point on …
incompressible flow

Worldtech Asked on 28th December 2018 in Fluid dynamics.
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- 1 answers
- 0 votes

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