High-order Navier–Stokes · GPU
HAVA-HYPERFDX1
Time-accurate solver for hypersonic reacting flows with high-order schemes and on-the-fly rendering.
- ~30× vs multi-node CPU
- 300M grid points on one GPU
Software
HAVA Laboratory · In-house codes
Software
GPU-accelerated solvers for hypersonic, rarefied and reacting flows, from kinetic DSMC to high-order Navier–Stokes and stability analysis, together with the simulations and verification cases behind them.
4solvers
–cases
–verification & validation
30–100×faster than CPU codes
Direct simulation Monte Carlo · GPU
HAVA-DSMCX1
Kinetic solver for rarefied and nonequilibrium flows: plumes, high-altitude aerothermodynamics and gas–surface interaction.
- 50–100× vs CPU DSMC
- Continuum to free-molecular
Linear stability · GPU
HAVA-STABLX1
Stability solver for compressible flows that maps disturbance growth and transition-sensitive regions.
- Tollmien–Schlichting & Mack modes
- Fast parameter sweeps
OpenFOAM-based · reacting flows
HAVAFoam
High-speed solver for compressible, reacting and hypersonic flows with detailed chemistry and adaptive mesh refinement.
- RANS & LES
- Adaptive mesh refinement
Simulations & verification
Moving rarefied flow at Mach 12
Complex moving rarefied-flow structures at Mach 12 resolved on a desktop workstation with an RTX 4090.
Mach 12rarefiedRTX 4090
Moving rarefied flow at Mach 12
HAVA-DSMCX1 resolving complex moving rarefied-flow structures at Mach 12. The simulation runs on a desktop workstation with an NVIDIA RTX 4090, capturing detailed flow physics at a fraction of the cost of conventional CPU-based DSMC implementations.
2 figures
Cylinder in thermal nonequilibrium against SMILE
Flow structure and stagnation-line profiles agree closely with the established SMILE DSMC solver.
VHS / VSSLarsen–BorgnakkeSMILE
Cylinder in thermal nonequilibrium against SMILE
Collision cross sections use the Variable Hard Sphere (VHS) and Variable Soft Sphere (VSS) models, and energy exchange between translational and internal modes uses the Larsen–Borgnakke approach, with relaxation rates from the Millikan–White and Parker models. The results are compared with the SMILE DSMC solver developed by the groups of Mikhail Ivanov and Sergey Gimelshein, and the two codes agree closely for this cylinder in thermal nonequilibrium.
Surface properties at 4 km/s and 68 km altitude
Heat flux, surface pressure, velocity slip and temperature jump for a 4 km/s free stream at 68 km.
heat fluxvelocity sliptemperature jump
Surface properties at 4 km/s and 68 km altitude
HAVA-DSMCX1 predicts a wide range of surface properties, including heat flux, surface pressure, velocity slip and temperature jump. The graphs show these quantities for a free-stream velocity of 4 km/s at an altitude of 68 km.
2 figures
Hypersonic re-entry at Mach 25
Re-entry capsule flow at Mach 25 with adaptive mesh refinement concentrated at the shock.
Mach 25AMRre-entry
Hypersonic re-entry at Mach 25
Hypersonic re-entry flow at Mach 25 computed with HAVAFoam. Adaptive mesh refinement concentrates cells where the gradients are largest, such as the bow shock, keeping the cost down while preserving accuracy.
Digital model of an expansion tube
Viscous simulation of the Rutgers expansion tube facility.
expansion tubeviscous
Digital model of an expansion tube
A digital model of an expansion tube facility, simulated with HAVAFoam including viscous effects.
High-Reynolds-number flow over a cylinder
Time-accurate hypersonic cylinder flow on ~300 million grid points, run in under 15 hours on a single RTX 4090.
300M grid pointsRTX 4090high order
High-Reynolds-number flow over a cylinder
High-Reynolds-number hypersonic flow over a cylinder computed with HAVA-HYPERFDX1 on a mesh of approximately 300 million grid points. The simulation took less than 15 hours on a local PC equipped with an RTX 4090, and the flow field was rendered on the fly during the run, without separate post-processing.
3 figures
Mach 4 cylinder wake against the Caltech experiment
Reproduces the dominant wake frequencies and Strouhal numbers of Prof. Shepherd's Mach 4 experiment at Caltech.
Mach 4wake transitionStrouhal number
Mach 4 cylinder wake against the Caltech experiment
Supersonic flow over a cylinder at Mach 4 was investigated experimentally by Prof. Shepherd's group at Caltech, and HAVA-HYPERFDX1 was validated against the same case. The configuration is particularly challenging because the wake shows the onset of transition to turbulence. The solver reproduced the dominant wake frequencies and the corresponding Strouhal numbers, and the predicted surface quantities agree closely with our in-house OpenFOAM-based solver, which is about 30 times slower. Current work adds real-gas effects, thermochemical nonequilibrium models and wall models for LES.
2 figures
Growth rates over a flat plate at Mach 6
Stability maps of disturbance growth and decay for hypersonic flow over a flat plate.
Mach 6Mack modeslinear stability
Growth rates over a flat plate at Mach 6
Growth rates for hypersonic flow over a flat plate at Mach 6, computed with HAVA-STABLX1. The maps show where disturbances grow or decay across frequency and wavenumber, tracking the dominant instability modes.
2 figures
Neutral curves at Mach 4 and Mach 8
Comparison with existing stability data for Mach 4 and Mach 8 flows.
Mach 4Mach 8neutral curve
Neutral curves at Mach 4 and Mach 8
Validation and verification studies of HAVA-STABLX1 are ongoing. These graphs compare the computed results with existing data for Mach 4 and Mach 8 flows.
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