CFD Training Package of Aerodynamic & Aerospace
Aerodynamic & Aerospace CFD training package by ANSYS Fluent software.
Aerodynamic & Aerospace CFD Training Package
Following is the Aerodynamic & Aerospace CFD training package:
This terrific package includes ten different CFD simulation, associate with aerodynamic and aerospace engineering field as following:
This project is going to simulate a NACA 0012 airfoil in the compressible airflow field. In the present case, the attack angle is 5 degrees. The purpose of this project is to investigate the behavior of airflow and the pressure distribution around the airfoil, as well as to study the drag and lift forces. The Mach number is equal to 0.6 in the present case.
The project aim is to investigate the pressure distribution and flow behavior around a rotating dimpled cylindrical wall. We are going to simulate airflow in a rectangular channel. A cylindrical object is placed in the channel. The airflow enters the rectangular channel at a horizontal velocity of 0.45 m/s, and it collides with the cylindrical body. The cylindrical body rotates at an angular velocity of 20 radians per second (rad/s) around the central axis. The cylinder wall has dimples. Therefore, the presence of dimples on the cylinder surface effects on the fluid behavior.
The present project concerns the simulation of airflow around a NACA 0015 airfoil considering the MHD effect. This airfoil is a symmetrical airfoil that does not produce a lift force at zero attack angle, and we investigate the lift coefficient of this airfoil at different attack angles with and without magnetic (MHD) force. In this problem, we study the separation and the maximum angle of attack where the separation does not occur. By applying the magnetic force (MHD), the separation happens at the larger attack angle of attack.
The present study simulates airflow within a supersonic convergent-divergent nozzle and examines the behavior of airflow separated from the nozzle in the surrounding environment and shock wave. The value of the nozzle pressure ratio in the current system is 1.5, and the amount of inlet air pressure is 153580.65 Pascal (NPR = P / P_ambient = 1.5 and therefore P = 1.5 * 102387.146), as well as the pressure at the output, is equal to the ambient pressure, that is 102387.146 Pascal. Also, the inlet airflow has a temperature of 290 Kelvin.
The functional structure of the nozzle is such that as the fluid enters it and passes through the convergent part of the nozzle, according to the continuity equation, it causes the velocity of the passing fluid to increase by decreasing the cross-sectional area of the flow. Therefore, due to Bernoulli’s law, the fluid pressure decreases with increasing velocity, consequently. Parameters such as Mach number, velocity, and pressure based on the motion of the fluid flow in the longitudinal direction of the nozzle have been investigated.
The present problem deals with the flow of water vapor as the main fluid (primary) and the secondary fluid (suction) within a convergent-divergent ejector. The purpose of the present simulation is to investigate the behavior of primary and secondary fluid after passing through the internal convergent-divergent nozzle and the ejector diffuser. In the current model, due to the vacuum pressure difference between the two inlet fluids, the suction phenomenon for the secondary fluid has to occur. The Mach number of the fluid flow inside the ejector increases as well. To analyze this model, we investigate parameters such as Mach number, velocity, and pressure based on the motion of the fluid flow along with the ejector.
The present study deals with the airflow on the HAWT blades. The purpose of the problem is to study the distribution of velocity and pressure on the surface of the blades and on their body. There are three areas around the blades for airflow. There is an area around the blades, an area in the front of the blades, and an area behind the blades. The airflow behaves normally in the front and behind the blades, while in the area around the blades, the rotational motion of the blades causes the rotational flow.
in this case, there are two steps for the reaction of methane burning with Oxygen, with six species involved in the reaction, namely: methane, Oxygen, nitrogen, water vapor, carbon dioxide, and carbon monoxide. The air mass flow inlet is 0.02 kg. s-1 and inlet air temperature is equal to 300 k. Mass fractions are .23 and .77 for Oxygen and nitrogen, respectively. The fuel is methane, and its inlet temperature is 300 k; also, the flow rate is 0.0006 m. s-1.
In this project, we simulate the supersonic airflow encountered by a double-wedge oblique airfoil barrier passing through a channel. The airflow in the simulation environment around the obstacles and canals has a temperature of 129.46 Kelvin and a Mach number of 2.49. Ultrasonic airflow hits a diagonal barrier in its path, and then passes through the inner space of the square channel, and the collision with the sharp obstacle creates a shock wave. The present study aims to investigate the air pressure and velocity distribution around the barriers and inside the canal and also to study the shock wave phenomenon. It should be noted that since the present problem is done in the unsteady state, its time step is considered to be 0.025 seconds, and the total time of the simulation process is 0.75 seconds.
The problem is going to simulate the airflow inside an axial flow compressor (Rotor Nasa 37). The present model consists of a series of blades for an axial-flow compressor connected to the central axis within a cylindrical area. Only one row of rotating blades is drawn on the central rotor of the compressor, to simplify the simulation model. The blades rotate around the central axis at a rotational speed of 14043 rpm. Also, the mass flow rate of the air passing through the compressor is 33.25 kg/s. The purpose of this project is to investigate the behavior of airflow and the pressure distribution around the blades after compression by the compressor.
Since the turbine produces work by converting thermal heat energy into mechanical energy, increasing the temperature and initial pressure of the fluid increases the heat energy of the fluid, thereby increasing the rate of conversion of thermal energy into mechanical energy and ultimately increasing work production. Therefore, one of the most important issues related to turbines is to study the cooling systems of turbine blades to increase the efficiency of turbine operation, reduce the thermal stresses caused by high temperatures on the surface of the blades and finally increase the blades lifetime. One of the most common methods of cooling in turbines is to use hollow blades. It means to make the inside of the blades empty to flow the coolant or airflow.
CFD Training Package
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CFD Training Package
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MRCFD is going to surprise you by offering comprehensive CFD training packages.
These fantastic packages contain various CFD simulations and training movies. Also, you will benefit from free two-week technical support after buying every CFD training package.
CFD Training Package
Following are the CFD training package topics by MRCFD:
CFD Training Package
- Aerodynamic & Aerospace
- Electrical & power
- Hydraulic structure & civil
- Dynamic mesh
- MHD & EHD
- Mass transfer
- Moving mesh
- Solidification & melting
- Source term
- Species transport
- Thermal FSI
- Heat Exchanger
- Compressible flow
- Nano fluid
- Heat transfer
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