Learn Computational Fluid Dynamics using ANSYS Fluent

Explore how CFD unlocks aviation insights by using ANSYS Fluent to optimize aerodynamics, aircraft components, and propulsion while saving time and money through flow physics.

Learn how numerical experiments with CFD using ANSYS Fluent act as a design tool, simulating fluid flow and predicting aerodynamic performance, bridging wind tunnel data with digital models.

Learn how the continuity, momentum, and energy equations govern fluid flow, how CFD discretizes them as integral or PDE-based, coupled nonlinear algebraic systems solved iteratively on computers.

Explore how ANSYS Fluent uses density-based and pressure-based solvers to tackle high- and low-speed compressible flows, detailing momentum, continuity, and energy equations within a control-volume framework.

Discover how a pressure-based solver enforces mass conservation via a pressure equation derived from continuity and momentum, using a projection method to update velocity and compare segregated and coupled algorithms.

Explore the pressure based segregated algorithm, solving velocity, pressure, temperature, and turbulence sequentially in a memory-efficient, decoupled cycle. Learn how iteration updates momentum, pressure correction, and energy equations to converge.

Learn how the pressure based coupled algorithm solves momentum and continuity simultaneously with updated properties, yielding faster convergence than the segregated approach, at the cost of higher memory usage.

Explore the density based solver for high speed compressible flows, solving continuity, momentum, energy, and species equations together to handle variable density and supersonic conditions with iterative convergence checks.

Explore density-based solver formulations, solving coupled nonlinear equations (continuity, momentum, energy) via implicit or explicit linearization, producing block systems solved with ilut/amg to update pressure, velocity, and temperature fields.

Explore density-based explicit formulation in ANSYS Fluent, solving for pressure, velocity, and temperature one cell at a time, contrasting explicit per-cell updates with implicit schemes that use neighbor values.

Explore the difference between laminar and turbulent flow, why turbulence models are needed in CFD, and how ANSYS Fluent handles complex flows with practical modeling approaches.

Explore how turbulence models in ANSYS Fluent replace small-scale eddies with averaged equations, solving for added unknowns using epsilon, omega, and transition models to balance accuracy and cost.

Explore turbulence modeling with Reynolds-averaged Navier-Stokes equations, including mean-fluctuating decomposition, and learn to choose models based on physics, accuracy, and computational resources.

Open the ANSYS Workbench window, create and rename a project such as a pipe project, and follow the five-module workflow: geometry, setup, meshing, solving, and results for fluid flow simulations.

Learn to model a two-dimensional pipe geometry in ANSYS Fluent using design modeler, creating a rectangle, setting dimensions, generating surfaces, and importing external CAD geometries.

Model a two-dimensional geometry in SpaceClaim by switching from 3D to 2D and creating a rectangle on the XY plane, with the origin as reference.

Create a simple CAD rectangle, save in STEP format, and import the geometry into ANSYS Workbench using Design Modeler or Space Claim to set up a 2D domain for simulation.

We define a pipe domain with inlet, outlet, and walls in ANSYS Fluent and begin the grid generation step using the meshing module.

Learn how to create and refine a mesh for a rectangular domain in ANSYS Fluent, using automatic and face meshing, edge sizing, and naming inlet, outlet, and walls.

Learn how to set up a Fluent simulation: save and reopen projects, configure double precision, select laminar flow, apply boundary conditions, initialize, run iterations, and monitor convergence.

Visualize the flow field in ANSYS Fluent by viewing velocity contours and vectors, using the legend to show blue for zero velocity, with inlet 0.10 m/s and outlet 1.34 m/s.

Explore how pressure definitions in ANSYS Fluent affect simulations, including gauge and absolute pressure, operating pressure, boundary conditions, and velocity specification for subsonic and supersonic flows.

Master spatial discretization with the control volume method to convert transport equations into discrete, conservation-based forms. Explore convection and diffusion discretization using face values and upwind schemes, including second-order options.

Explore simulating external supersonic flow around an axisymmetric bluff body in ANSYS Fluent, with Mach 2 and a bow shock, and geometry creation via design modeler or us grill.

Create a semicircular domain in the design modeler by sketching on the x–y plane, setting millimeters, and using a 7.5 mm radius to form a closed loop for surface creation.

Create a surface from a sketch in ANSYS Fluent, ensuring a closed loop for meshing, then generate a structured mesh by dividing a mixed rectangular and circular domain into sections.

Create a straight line in a sketch on the XY plane to divide the surface into two phases, using line from sketches to define the domain for a structured mesh.

Create a 2d space claim geometry in the xy plane, sketch an arc and lines with precise dimensions, and save milestones to prepare the domain for meshing.

Apply SpaceClaim's split tool to divide a surface into two phases, selecting edges and a horizontal line to create distinct geometry for numerical experiments.

Create a CAD domain by sketching an arc with radius seven point five and straight lines, extruding, saving as a STEP file, then importing the geometry into Fluent's design modeler.

explore how density varies with flow regime using the ideal gas law in ansys fluent, comparing constant density, compressible ideal gas law, and polynomial or piecewise-linear density models.

Learn to create a structured grid in a 2D ANSYS Fluent model by configuring surface and edge meshing, setting divisions, and generating a balanced mesh for accurate results.

Create named boundaries in an ANSYS Fluent project by naming the four-body and real-body sections, defining an axis, and assigning edge and outlet boundaries before updating the mesh.

Configure the numerical scheme with double precision and parallel processes. Use a density-based solver for axisymmetric supersonic flow and enable energy and k-omega turbulence with ideal gas density.

Learn how to choose and configure solution methods in a density-based ANSYS Fluent model, including implicit vs explicit formulations, second-order schemes, transient options, and convergence monitoring.

Increase the CFL number and examine how it affects stability and residual convergence in ANSYS Fluent, with attention to pressure behavior and convergence thresholds.

The simulation converged after about 7000 iterations, with convergence depending on setup, turbulence model, and mesh size. Pressure stabilized; residuals leveled off, indicating no further changes in the domain.

Compute the coefficient of drag from ANSYS Fluent by extracting drag force, density, velocity, and reference area, and compare boxy versus sleek body designs.

Explore contours and velocity fields to identify bow shocks around a blunt body using mag contour and vector displays. Discuss how domain size and mesh refinement affect shock resolution.

Create plots to visualize pressure variation along the x direction vector on a selected surface in ANSYS Fluent; save the plot and compare results across surfaces.

Learn to use the post-processing module in Fluent to create contours, vectors, and streamlines on planes, visualizing velocity, pressure, and temperature fields from CFD data.

Create a line on a surface with bodyline, intersect it with a plane to form the line, then plot pressure variations along that line by configuring the chart.

Verify the mass flux with the flux report, confirm the continuity equation by ensuring mass entering equals mass leaving at the inlet and outlet, and check the mass flow rate.

Verify compressible flow simulations in ANSYS Fluent by applying normal shock relations to compare pre- and post-shock values (Mach, temperature, pressure) using a calculator and probe.

Explore numerical experiments on a blunt body with a spike and aerospike, using 2D symmetric modeling in ANSYS Fluent to study bow shock, drag, and 3D physics approximation.

Model the two-dimensional domain of the blunt body with an aerospike in design modeler, set boundary conditions, turbulence model, and numerical methods, and plan a structured mesh.

Divide a complex domain into multiple segments using straight lines, arcs, and sketch-based lines, ensuring equal segments on adjacent regions and correct surface selection for meshing.

Learn grid generation in ANSYS Fluent by creating surface meshes, applying edge sizing, and naming regions like inlet and outlet; explore grid density via a grid independent study.

Set up physics in ANSYS Fluent for a supersonic axisymmetric flow using density-based model, energy equation, k-omega standard turbulence, ideal gas law, and proper boundary conditions with autosave and initialization.

Analyze residuals and monitor pressure across iterations to assess convergence of continuity, x- and y-velocity, momentum, and energy equations in ANSYS Fluent.

Explore how increasing the CFL number influences convergence in ANSYS Fluent simulations, reducing residuals and stabilizing the pressure behavior over many iterations.

Compare CFD results with experimental data for an aerospike and blunt-body models by analyzing pressure coefficients, mesh refinement effects, and convergence trends, using data extraction and plotting to assess accuracy.

Compare the aerospike and black body simulations, analyze drag reduction and recirculation zones, and visualize velocity and temperature fields to assess post-processing results.

Replicate the cone and cylinder aerodynamics study in CFD with ansys fluent, using 2d simplification and 3d simulations at Mach 2 and -2 to 12 degrees.

Model the nose-cone geometry in Design Modeler for a two-dimensional ANSYS Fluent simulation, define the 34 mm diameter nose and 17 mm upper half, and create a structured mesh.

Set up a density-based solver for high-speed flows in Fluent, enable the energy equation, and apply the active symmetric form, pilot Almeida's model, and Whiskas turbulence model.

Learn how to assess convergence in ANSYS Fluent by tracking residuals and pressure stability, and refine the mesh to improve drag coefficient comparison with experimental data.

Compare experimental results with CFD in ANSYS Fluent, focusing on the drag and axial coefficients, Mach number, and expansion fans. Learn mesh refinement and convergence to validate results.

Compare results from different grids in ANSYS Fluent to assess grid refinement and grid independence, validate the drag coefficient against reference data, and discuss turbulence model choices and result validation.

Learn grid generation in ANSYS Fluent and apply biasing to refine elements near geometry, controlling edge sizing and divisions for the region of interest.

Compare 3d and 2d simulations in ANSYS Fluent, detailing boundary conditions and mesh design, and show how angle of attack and shock waves affect axial, normal, and moment coefficients.

Explore how changing the angle of attack affects a supersonic airfoil geometry in a simple ANSYS Fluent case, setting boundary conditions and adjusting the geometry for different angles of attack.

Create a two-dimensional wing domain in design modeler with a 10-degree angle and constant cross-sectional area. Split the domain into segments and prepare for meshing along the axis of symmetry.

Master grid generation for Fluent simulations by building surface meshes, applying sizing and division controls, and biasing to place denser elements near critical regions of the model.

Set up a density-based solver for a zero-degree angle of attack supersonic case, enable the energy model, and apply pressure-far-field boundaries at Mach 3, then initialize and run the simulation.

Observe a converged ANSYS Fluent flow with shock waves around a wedge and residues below 1e-3, then replicate angle of attack cases by adjusting boundary conditions.

Verify supersonic flow results in ANSYS Fluent by using theta-beta-mach charts to predict wave angles for various deflection angles and Mach numbers, and compare pressure distributions via post-processing.

Explore rocket engines, including solid and liquid propellants, the combustion chamber, and nozzle, and how exhaust plumes convert energy into thrust, with considerations of plume expansion for numerical simulations.

Demonstrate simulating a rocket engine's internal flow by turning a 2D sketch revolved around a central axis into a symmetric 3D model and applying fluent symmetry to reduce to 2D.

Divide the domain into segments with Space Claim, import the step file, and visualize the geometry to set up a uniform structured mesh in the meshing module.

Divide the model surfaces into zones, apply face meshing with quadrilateral elements, and adjust edge divisions to refine critical regions for simulating rocket nozzle exhaust flow in ANSYS Fluent.

Analyze rocket engine boundary conditions through hand calculations, estimating chamber pressure, temperature, density, and exit throat areas, then compare results with a compressible aerodynamics calculator.

Set up a density-based fluent 2d axis case, enable the energy equation, use the k-epsilon realizable model with ideal gas density, and configure pressure inlet and outlet.

Monitor residuals and extend iterations to verify convergence as the solver moves from initial reverse flow with rigid boundaries to a stabilized solution.

Compare hand calculations with CFD results in ANSYS Fluent, verify convergence and residual criteria, and confirm exit Mach number, pressure, and temperature using results post and data file quantities.

Extend the domain beyond the nozzle to capture the rocket plume, using a surface 5–8 times the exhaust length and 1.5–2 times the diameter; note licensing limits.

Create the domain in space claim for a 2D geometry, set dimensions for the nozzle and exhaust, and extend the domain to avoid reflections before grid generation in ANSYS Fluent.

Mirror the body across the middle plane to replicate geometry, create the surface for meshing, and divide the domain into rectangles while splitting surfaces to prepare the mesh.

Discretise the domain in ANSYS Fluent by selecting faces and edges, splitting surfaces, and setting mesh size to achieve target cell counts while considering symmetry and 2D versus 3D cases.

Set up the physics in ANSYS Fluent by selecting density-based energy with realizable k-epsilon and ideal gas density for supersonic flows; configure inlets and zero operating pressure.

Verify convergence in ANSYS Fluent simulations by inspecting iterations, refining the mesh to address viscosity ratio warnings, and analyzing the flow field and nozzle exhaust plumes.

Learn to visualize CFD results in ANSYS Fluent post processing, plotting temperature and velocity fields on planes, creating and animating streamlines, and exporting motion videos.