Filter
9 cases

Aerospace

5 cases
NLF Airfoil — skin friction visualization
Aerospace
NLF Airfoil
NLF(1)-0416 natural laminar flow airfoil validated with the Amplification Factor Transport transition model against NASA TP-1861 wind-tunnel data.
SCWS Common Research Model
Aerospace
SCWS Common Research Model
Static alpha sweep and unsteady rolling case from the AIAA S&CPW2 stability-and-control workshop, validated against NASA Langley 12-Foot Tunnel data.
XV-15 tiltrotor in hover
Aerospace
XV-15 Rotor Hover Validation
Multifidelity rotor hover study (BET disk, BET line, DDES) across five collective pitch settings, with thrust, torque, and figure of merit compared to experiment.
Blue Scout launch vehicle
Aerospace
Blue Scout Launch Vehicle
Automated transonic alpha-Mach sweep on a slender-body rocket, validating axial, normal, and pitching-moment coefficients against NASA TN-D-1958.
Hammerhead launch vehicle
Aerospace
Hammerhead Launch Vehicle
Supersonic Mach sweep at fixed 2° incidence comparing axial and normal force coefficients against wind-tunnel data for a hammerhead fairing geometry.

Marine

1 case
DARPA Suboff fully appended submarine
Marine
DARPA SUBOFF
Bare-hull submarine resistance across a six-speed sweep (5.93–17.79 knots), comparing steady SA RANS and SA-DDES against DTRC towing-tank data.

Wind Energy

1 case
DTU 10 MW Reference Wind Turbine
Wind Energy
DTU 10 MW Reference Wind Turbine
SA-DDES sliding-mesh rotor study at below-rated wind speeds (8–11 m/s), comparing shaft power, thrust, and spanwise sectional loads to DTU CFD reference data.

Fundamental

2 cases
2D CRM High-Lift configuration
Fundamental
2D CRM High-Lift
Multi-element high-lift configuration validated against NASA 3rd AIAA High Lift Prediction Workshop data with slat and flap deployed.
ONERA M6 Wing surface pressure
Fundamental
ONERA M6 Wing
Four-level grid convergence study at Mach 0.84, Re 11.72 M, α 3.06°, comparing forces, surface Cp, and Cf against NASA TMR reference CFD and experiment.
01
100×
Faster than CPU solvers
GPU-native architecture eliminates the CPU bottleneck. Full-aircraft simulations that took days now complete in hours on the Flexcompute cloud.
02
Python
Full API and automation
Flow360 is fully scriptable. Case setup, mesh submission, post-processing, and result extraction all accessible through the Flow360 Python client.
03
Validated
Against published benchmarks
Every published case compares Flow360 output against experimental data or reference solutions from AIAA workshops, NASA datasets, and academic literature.

Run your own validation cases on Flow360

Access the full solver on the Flexcompute platform or talk to an engineer about your use case.

Explore Flow360 Talk to an Engineer