New CFD tutorials and examples

Computational fluid dynamics is the engineering version of a wind tunnel built in software: you draw the shape, split the air around it into tiny cells, and let the equations for momentum and pressure predict what the flow will do. OpenFOAM is one of the best-known open-source tools for that job, and ParaView is a standard viewer for turning the results into slices, streamlines, and pressure maps. (openfoam.com) (docs.paraview.org) The hard part is not pressing “run.” The hard part is setting the domain size, the mesh, the wall spacing, and the solver controls so the answer reflects physics instead of your setup mistakes, which is why tutorials that show the full workflow are more useful than isolated screenshots. (openfoam.com) (github.com) Patrick Hanley’s recent UAV walkthrough is useful because it starts with a stereolithography, or STL, geometry file and shows the whole path to aerodynamic loads and pressure contours instead of stopping at import. His published overview says the workflow uses automatic domain sizing from the geometry, default solver settings, and visualization aimed at getting a baseline result quickly. (hanleyinnovations.com) (youtube.com) That matters in small-aircraft work because unmanned aerial vehicles usually live in a design space where one wingtip tweak or fuselage bump can change drag and stability before a prototype ever flies. A reproducible “geometry to contour plot” example is the kind of artifact a hiring manager can inspect line by line. (youtube.com) (hanleyinnovations.com) A second shared example focuses on near-stall flow with flaps down. Stall is the point where the airflow no longer follows the wing smoothly, like water peeling away from the back of a spoon, and flap deflection changes that separation pattern by increasing wing camber and local loading. (openfoam.com) (journal.openfoam.com) That is where ParaView earns its keep, because a stalled wing is hard to understand from a single lift number. ParaView’s standard computational-fluid-dynamics workflow includes slices, stream tracers, and contour views that let you see where the separated region starts and how it grows across the airfoil or flap. (docs.paraview.org) (su2code.github.io) The technical value of a near-stall case is verification and validation. Verification asks whether your mesh and numerics are solving the equations correctly, while validation asks whether those solved equations match real flow behavior, and both become more demanding once separation appears. (journal.openfoam.com) (openfoam.com) The third shared explainer uses the Lockheed SR-71 to teach static margin. Static margin is the distance between where the airplane’s mass acts and where the aerodynamic restoring force effectively acts, and it works like balancing a shopping cart: put the weight in the right place and it tracks straight, put it in the wrong place and it wants to wander. (aircraftflightmechanics.com) (mae-nas.eng.usu.edu) The SR-71 is a good teaching case because it flew above Mach 3 and had stability-and-control behavior NASA later documented in flight-test reports. NASA’s technical publication on the aircraft shows how stability and control estimation were extracted from real test data, which gives a concrete bridge between textbook pitch stability and an aircraft people actually recognize. (nasa.gov) Put together, these three resources cover the three things interviewers usually probe separately. One shows setup discipline on a full unmanned-aircraft geometry, one shows flow-visualization skill around stall, and one shows that you can explain stability in plain language with a famous airframe instead of hiding behind equations. (hanleyinnovations.com) (docs.paraview.org) (nasa.gov) That is why these posts are more than “cool CFD.” They are ready-made project skeletons: import a shape, justify the mesh, visualize the separated flow, and then explain what the result means for stability and design in words a non-specialist can follow. (youtube.com) (journal.openfoam.com) (aircraftflightmechanics.com)