Compressible Flow – ANSYS Fluent Training Package, 10 Practical Exercises for ADVANCED Users
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Compressible Flow CFD Simulation Package, ANSYS Fluent Training for ADVANCED Users
This CFD training package is prepared for ADVANCED users of ANSYS Fluent software in the COMPRESSIBLE FLOW area including 10 practical exercises. You will learn and obtain comprehensive training on how to simulate projects. The achieved knowledge will enable you to choose the most appropriate modeling approaches and methods for applications and CFD simulations.
Compressible Flow occurs in many industrial devices and applications. some of these cases are investigated in this training package.
Problem 1 simulates the air compression inside a Rampressor. The Rampressor is a unique type of ultrasonic compressor rotor that operates at a high-pressure ratio, and engine technology and gas compression are the ramjet ultrasonic shock wave. The operating mechanism of these compressors is such that the gas flow passes through a fixed outer cover and a sloping surface or inner ramp.
Problem 2 simulates compressible flow around an aerial structure considering Large Eddy Simulation (LES). A density-based approach has been used to define the type of airflow solution around this aerial structure; Because the existing airflow is entirely compressible.
Project 3, supersonic flow over an F-16 aircraft considering inviscid fluid was simulated, and then the results were investigated. Supersonic speed is the speed of an object that exceeds the speed of sound. It is estimated to be around 343 m/s in the dry air at a temperature of 20 C.
In project 4, aerodynamic coefficients of a Formula One (F1) car by two different solvers of pressure-based and density-based, have been studied, at a speed of 108 meters per second at a lateral angle of zero degrees (actually a straight path). This velocity at the ground level is equivalent to Mach number approximately 0.32. We know this area from Mach number is the transition zone from incompressible to compressible flow, so on this geometry, the drag coefficient is investigated using two pressure-based and density-based solvers is discussed.
Problem 5 simulates the process of condensation inside a steam ejector. When the Wet Steam multiphase model is used, two sets of transport equations are solved: the mass fraction of the condensed liquid phase and the number or concentration of droplets per unit volume.
Paper Numerical Validation (Compressible Flow)
In project 6, we simulated the compressible flow around the NACA0012 airfoil, and then we compare the results with the results extracted from an article called this “Numerical Simulation OF VISCOUS TRANSONIC AIRFOIL FLOWS”.
Problem 7 simulates the water vapor flow inside a steam ejector. This numerical simulation is based on the reference paper “CFD simulation on the effect of primary nozzle geometries for a steam ejector in refrigeration cycle” and the results of the present numerical work are compared and validated with the results in the reference article. An ejector is a mechanical device that uses an actuator fluid to suck a secondary material (gas, liquid, or solid particles), and finally, the actuator fluid and the suction substance are mixed together and exit from the system.
Problem 8 simulates the two-dimensional compressible flow field through a transonic linear turbine cascade. The present project’s results are compared with experimental results of the paper “Midspan Flow-Field Measurements for Two Transonic Linear Turbine Cascades at Off-Design Conditions”. Turbulence modeling and Computational procedures (boundary conditions, etc.) are simulated based on the article “Numerical study of the flow field through a transonic linear turbine cascade at design and off-design conditions”.
Acoustic (Compressible Flow)
Problem 9 simulates the acoustic wave and the sound produced inside a Turbojet. The model includes a turbojet that has a fan in its inlet. This fan is rotating at 2000 rpm and around the X-axis in the current model.
Finally, in project 10, the flow inside a NACA0012 airfoil is first has been simulated. The angle of attack is 1.53 degrees and the simulation has been done by the density-based solver due to the compressibility with a Mach number equal to 0.7. Then the geometry is optimized to improve lift to drag (L/D) as aerodynamic efficiency.
You can obtain Geometry & Mesh file and a comprehensive Training Movie that presents how to solve the problem and extract all desired results.[/vc_column_text][/vc_column][/vc_row]
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