CFD Analysis of Aircraft Wing

learn to build a 3D CAD model of the Onera M6 wing from airfoil coordinates, with millimeter units and a swept, symmetric wing using 0.56 taper ratio in Creo Parametric.

Create two airfoil sections in millimeter units, set up a coordinate system, import coordinates, and blend the sections to form a wing with a defined span.

Learn to compute tip chord from root chord using taper ratio, create and align two airfoil sections, blend them into wing geometry, and export a step file for Ansys simulation.

Open Ansys workbench, import the STEP file, and set up geometry, mesh, and CFD domain for fluent, including inlet boundary conditions and the coordinate system.

Create a wing domain using symmetry, revolve a centered arc to 90 degrees, extrude to five meters, and mesh for CFD, solving continuity, momentum, energy equations with turbulence models.

Import a 3D CAD model into Fluent Design Modeler, assign a domain material, and subtract the imported wing geometry to form the surface using boolean operations.

Assign boundary conditions on wing surfaces and refine the mesh in Ansys fluent with a body of influence to target regions, comparing default meshing options.

Divide the wing's upper surface into multiple segments using lines from sketches and projections in the ANSYS workbench geometry module, creating three regions: leading edge, middle, and trailing.

Suppress stray line bodies in the design modeler to prevent them from entering the meshing module, keeping the domain and subtracted surfaces clean for accurate CFD analysis.

Master advanced meshing for a wing by applying face sizing and element sizes, configuring ten inflation layers with total thickness, and naming key surfaces for fluent setup.

Configure the flow physics by selecting a pressure-based steady solver, enabling energy and turbulence models, and setting boundary conditions with Mach 0.3895 and 3.06-degree angle.

Set up wing CFD run by selecting the reference zone, using a coupled second-order pressure-velocity scheme with pseudo transient simulation and high-order relaxation, and monitor residuals with a 1e-3 criterion.

Assess convergence by examining residuals of the x, y, and z velocity and the constant pressure along the surface, indicating the simulation was performed with the correct method.

Explore CFD post visualization in Ansys workbench, visualize wing pressure and velocity fields, and export results to Tecplot or Paraview, while plotting contours and vectors on cutting planes.

Mirror the wing in CFD post to compare contour data with reference results from the Onera M6 wing validation, using symmetry reflections and pressure contours.

Plot pressure variation along the aircraft wing using fixed pressure taps, create planes and polylines in CFD post, and export solution data as a CGNS file for Tecplot analysis.

Open the CFD post and verify the pressure coefficient chart by setting the variable to pressure coefficient, then observe the wing-wide variation as the y-axis scales from -1.5 to 1.

Invert the pressure coefficient axis to align the chart with wing surfaces, convert x to x over L, and prepare a variable expression to compare CFD results with experimental data.

Create a chord line from the leading to the trailing edge, normalize its x coordinate, and plot the pressure coefficient versus normalized x for CFD and experimental results.

Compare experimental and CFD pressure coefficient data for an aircraft wing using Origin to create a high-quality chart, invert axes for surface orientation, and digitize plots for accurate overlay.

Export experimental data from Origin as a CSV file, import into CFD post, and compare with CFD data to verify the numerical setup.

Import a cgns file from Fluent Solver into Tecplot 360 to visualize the surface pressure field with contour styling, rotate and zoom, and refine with temperature contour.

Explore iso surfaces and Mach contours to visualize transonic flow, shock waves, and velocity traces around the wing using isosurface values and stream lines.

Explore Tecplot to enhance CFD visualization of wing flow by customizing slices in x, y, z, showing Mach contours, and animating stream traces to reveal airflow around the wing.