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Fixed-Price - Intermediate ($$) - Est. Budget: $30 - Posted
I am tasked to do a CFD simulation analysis of an ice cream batch freezer. The purpose of this analysis is to study how the fluid flow of the ice crystals formed on the barrel wall can affect the growth of the ice crystals. The fluid flow varies in accordance to the ice cream composition mix and the operating parameters of the dasher (e.g. rotational speed). I also have to take note of the temperature of the process. The simulation has no inlet and outlet since the ice cream exits where it exits. For further enquiries please add me on Skype. I'll pay more if the job is satisfactory.
Skills: ANSYS Computational Fluid Dynamics (CFD)
Fixed-Price - Intermediate ($$) - Est. Budget: $25 - Posted
translate the attached code in matlab to ansi C. It is required to translate command by command not use internal features of matlab to execute commands in C.you can add me in s-kype imran777467.i have short time so be quick .
Skills: ANSI C MATLAB Translation
Fixed-Price - Intermediate ($$) - Est. Budget: $30 - Posted
It is required to attain results similar to that obtained in the document 'Static and dynamic analysis' or 'UR2'. *Should be an expertise in ANSYS APDL. *Further queries can be discussed over exchange of mails. ... The specific requirement has been highlighted in the attached PDF. We need four different log files (ANSYS APDL log file or script file) which produce the same result as in the highlighted part.
Skills: ANSYS Computer-Aided Design
Fixed-Price - Entry Level ($) - Est. Budget: $150 - Posted
For this project, you have to show Transonic Airfoil analysis over a range in Mach numbers to see the effect on lift and drag coefficients. Follow the tutorial, but set the far-field freestream conditions to sea level standard pressure and temperature. Then run the solution for Mach numbers at 0.5, 0.6 and 0.7, and then from 0.72 through 0.84 in increments of no more than 0.04. Record the lift and drag coefficients for each case to plot versus Mach number. After each solution, plot a contour plot of Mach number over your airfoil and save it. You can save images of the graphics window by using the "Save Pictures" button next to the file save icon in the upper left part of the window. Also, create an xy plot of Skin Friction Coefficient (under Wall Fluxes) to see if separation occurs (a negative shear stress) after the shock wave on the surface. Save this plot for inclusion in your report. Create a project report showing your lift and drag versus Mach number plots along with the Mach contour plots and surface shear stress plots.
Skills: ANSYS Computational Fluid Dynamics (CFD)
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