We have achieved remarkable technical advantages in complex scenarios such as large-scale multi-component full-aircraft unsteady computation, maneuvering attitude and dynamic analysis of moving components.
We have formed prominent technical advantages in complex scenarios including large-scale multi-component full-aircraft unsteady simulation, maneuver attitude and dynamic analysis of moving components, supporting key technology breakthroughs for sixth-generation fighters, hypersonic vehicles and other cutting-edge equipment. Meanwhile, in traditional aerodynamic performance evaluation, our solution achieves performance comparable to mainstream commercial software.
Adopts the technical combination of Turbulence-Model-Free Large Eddy Simulation (LES) + fully hexahedral mesh. 4th-order and above high-resolution spatial discretization (finite element/finite volume method) reduces numerical dissipation and directly resolves large-scale vortices without RANS turbulence model assumptions. It precisely captures complex flows such as shock waves and boundary layer separation under high angle-of-attack and massive separation conditions.
Built on the "Overset Mesh + Fully Asynchronous Computing" architecture, the simulation capability extends to billions of solving points with computation scaling linearly with problem size. Consumer-grade workstations can complete tasks originally requiring supercomputers. Combined with the Golden-Cross technology, consumer GPU workstations (e.g. RTX 4090) can run high-precision LES simulation, cutting hardware investment down to 1/100 of traditional supercomputing.
LES directly resolves unsteady flow and captures real transient details including pressure fluctuation and vortex shedding. It delivers engineering-decision-grade data for analysis and optimization of aerodynamic noise (e.g. landing gear / rotor noise) and flow-induced vibration (e.g. thermal fatigue of turbine blades), eliminating reliance on costly wind tunnel or physical tests.
Overset mesh technology accurately captures transient interference between moving components (such as fighter high-angle attack maneuver, eVTOL rotor-building interference, airliner landing gear retraction) and main structures. Coupled with fully asynchronous computing model, it avoids mesh distortion and convergence difficulties seen in traditional synchronous computing and boosts efficiency for large-scale transient simulation.
Based on the Space-Time Extended Kinetic Energy Conserving Flux Reconstruction Algorithm (STE-KEP-FR), it supports scaling up to billions of solving points. Computational cost grows linearly with problem scale and dimensional difference with full adaptivity without iteration. It enables system-level multi-scale coupled simulation (macro full-aircraft + micro details), such as full aero-engine computation and fluid-thermal-structure coupling for large aircraft wings.
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