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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
Seismic Retrofitting Contractor
Seismic Retrofitting Contractor, A very effective way of performing a seismic retrofit is to simply install hold-downs in all of …
JorgeKeel Asked on 4th August 2019 in Systems.
- 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
What is Y+ (Y plus) in CFD?
What is a y +(plus) value ?
Boundary layer

y plus

Worldtech Asked on 3rd August 2019 in Computational Fluid Dynamics.
- 2K views
- 1 answers
- 0 votes
Mach Number
What is a Mach number?
techAir Asked on 15th July 2019 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
Consider a two-dimensional duct with a straight horizontal lower wall, and a straight upper wall inclined upward through the angle 3 degree. Calculate the average flow Mach number over AB, assuming that M varies linearly along that portion of AB inside the expansion wave.
Calculate the average flow Mach number over AB, assuming that M varies linearly along portion AB inside the expansion wave.The …
Compressible flow

Expansion wave

techAir Asked on 4th July 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
What will be the maximum deflection angle through which a sonic flow can be expanded?
Calculate the maximum deflection angle through which a sonic flow can be expanded via a centered expansion wave.
Compressible flow

Sonic flow

Worldtech Asked on 4th July 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Maximum lift to drag ratio decreases as the Mach number increases. How to mitigate the effect of decrease in maximum lift to drag ratio when there is increase in Mach number.
How to mitigate the effect of decrease in maximum lift to drag ratio when there is increase in Mach number.
Airplane design

Supersonic flow

Worldtech Asked on 3rd July 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Consider the supersonic flow over a flat plate at an angle of attack. Outline a method to calculate the strengths of trailing edge shock and expansion waves, and direction of the flow downstream of the trailing edge.
Outline a method to calculate the strengths of trailing edge shock and expansion waves , and direction of the flow …
techAir Asked on 3rd July 2019 in Aerodynamics.
- 1K views
- 1 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

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