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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
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
Why sphere has a higher critical Mach number than cylinder?
Explain on a physical basis why the sphere has a higher Mcr than the cylinder.
techAir Asked on 2nd July 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
The airfoil section of the wing of the British Spitfire of world war II fame is an NACA 2213 at the wing root, tapering to an NACA 2205 at the wing tip. At what velocity is it flying for the root chord Reynolds number to be 9 x 10^6. Calculate the percentage of the profile drag coefficient that is due to pressure drag.
The airfoil section of a wing is an NACA 2213 at the wing root, tapering to an NACA 2205 at …
techAir Asked on 18th February 2019 in Aerodynamics.
- 3K views
- 1 answers
- 1 votes
Consider a diamond-wedge airfoil, with a half angle of 10 degree. The airfoil is at an angle of attack of 15 degree to a Mach 3 free stream. Calculate the lift and wave-drag coefficients for the airfoil.
Consider a diamond-wedge airfoil, with a half angle of 10 degree. The airfoil is at an angle of attack of …
Worldtech Asked on 17th February 2019 in Aerodynamics.
- 10K views
- 1 answers
- 0 votes
Consider a circular cylinder (oriented with its axis perpendicular to the flow) and a symmetric diamond-wedge airfoil with a half-angle of 5 degree at zero angle of attack; What does this say about the aerodynamic performance of a blunt body compared to a sharp – nosed slender body in supersonic flow ?
Consider a circular cylinder (oriented with its axis perpendicular to the flow) and a symmetric diamond-wedge airfoil with a half-angle …
techAir Asked on 16th February 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes

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