RE 104–108 · INCOMPRESSIBLE TO HYPERSONIC · OPENFOAM / SU2
Tensor Byte Labs Engineering Services runs high-fidelity CFD for aerospace and water/marine programmes — from external aerodynamics and aeroacoustics to hull resistance and offshore hydrodynamics. Led by a computational-aeroacoustics PhD who publishes the schemes we run in production.
// SERVICES
External aerodynamics, propulsion integration, and the aeroacoustics that certification and cabin-comfort teams actually get graded on.
Free-surface, hull, and process-water flows — where resistance, wake, and fatigue loading decide the business case.
// SOLVER STACK
No black boxes. Every result ships with the mesh, the solver settings, and a residual history you can check yourself.
Primary solver for incompressible and multiphase work: simpleFoam, interFoam, overInterDyMFoam for free-surface and moving-body problems.
Compressible and transonic aerodynamics with adjoint-based shape sensitivity, used for external aero and design-space exploration.
High-order, low-dissipation finite-volume schemes developed and published by our lead consultant — deployed when off-the-shelf dissipation would mask the physics.
Solver acceleration for large unsteady cases where wall-clock time is the actual constraint, not mesh count.
// REPRESENTATIVE ENGAGEMENTS
A sample of the class of problems we run. Cell counts and configurations are representative of production runs on comparable geometries.
Unsteady RANS on a 12M-cell hybrid mesh to resolve trailing-edge vortex shedding, coupled to a Ffowcs Williams–Hawkings acoustic analogy for far-field tonal noise prediction.
Free-surface VOF simulation across a Froude number sweep, dynamic trim and sinkage solved via 6-DOF coupling, validated against towing-tank resistance curves.
Unsteady 2D-strip and 3D URANS runs across the lock-in range to characterise cross-flow amplitude and fatigue loading ahead of a structural review.
Benchmarking a fourth-order CABARET scheme against standard finite-volume methods for compressible flows where numerical dissipation was masking real physics.
Steady-state simulation of a clarifier inlet fitted with a perforated distribution plate, tuning hole pattern and open-area ratio to eliminate short-circuiting and dead zones ahead of settling.
Single-passage RANS with mixing-plane rotor–stator interfaces to map horseshoe-vortex and passage-vortex loss generation and inform endwall contouring.
Multiple-reference-frame and sliding-mesh runs across the operating line to locate rotating-stall onset and quantify surge margin before a rig test was scheduled.
Density-based compressible RANS resolving the oblique shock train and separation bubble in a supersonic intake, with mesh convergence checked against a CABARET benchmark run.
// LEAD CONSULTANT
Head Researcher — Computational Fluid Dynamics & Aeroacoustics
PhD in Aerospace Engineering from Queen Mary University of London, where his research on flux-corrected, dispersion-improved CABARET schemes for wave propagation and computational aeroacoustics is published and cited across the field. His numerical methods work underpins the high-order solvers TBL deploys when standard schemes aren't accurate enough.
SELECTED PUBLICATIONS
// GET IN TOUCH
Tell us the problem, the industry, and the deadline — we'll scope the mesh and turnaround from there.