Stallion 3D: High-fidelity Aerodynamics Software
eVTOL Verification
Propwash, ground effect and complete aircraft insight
Aircraft Aerodynamics
CL, CD, CM and stability from the geometry
Real World Validation
Transonic validation and real engineering numbers
Transonic drag divergence
Verify subsonic, transonic & supersonic designs
UAV CFD
Cameras, stores, sensors and complete configurations
Compressible RANS CFD • Automatic grid generation • Case setup in seconds
* Stallion 3D requires MS Windows 10/11 (8 cores, 16 GB RAM recommended)
Benefits of Stallion 3D
Easy Case Setup • Actual Geometry Aerodynamics • Expert Support
- Import STL geometry from OpenVSP or your favorite CAD tool
- Automatic grid generation (repeatable across design iterations)
- Ideal for aircraft, UAVs, rockets, hydrofoils, and complex configurations
- CL, CD, CM and full force/moment breakdown for all 3 axes
- Stability‑relevant quantities to support operating decisions
- Pressure/Mach/velocity/temperature visualizations for reports
- 3D compressible RANS across subsonic, transonic & supersonic regimes
- k‑epsilon turbulence model (AoA 0–360°, crossflow 0–360°)
- Flux vector splitting for sharp shock capture
- Actuator discs (up to 100) for prop wash effects (RANS solver)
- Quasi‑steady surface rotation to compute stability derivatives
- Streamlines and slice plots with user‑controlled visualization
Setup in seconds • Get high-fidelity aerodynamics
Quick‑start tutorials to simulate aircraft, UAVs, rockets & more.
Real‑world validation
HIST (proprietary) + RANS/k‑epsilon for credible engineering results.
NACA 12% Wing
Experimental results from NACA Report No. 647. Comparisons of CL & CD vs. AoA show good agreement for the NACA 0012 wing.
Cessna 210
Experiment results from NASA Technical Report 2772. Comparisons of CL vs. CD, shows good agreement for the Cessna 210.
M6 Wing, y/b 0.8
ONERA M‑6 wing at M=0.8395, AoA=3.06°. Shown is the Cp distribution at y/b=0.8 which is often very difficult to validate.
HL-20 Lifting Body
HL‑20 at M=1.2, AoA=12°: NASA TM 4117 (CL = 0.48, CD = 0.24 & CM = -0.042) compares well with CFD (CL = 0.41, CD = 0.25 & CM = -0.0387)
Built to work on your laptop
Proprietary algorithms • High-fidelity CFD • Privacy • No hidden costs💰
Import geometry
Read in your aircraft design from OpenVSP or CAD (STL file).
Set conditions
Set speed, AoA, sideslip, altitude and simulation resolution.
Auto grid
Generate the volume grid automatically for repeatable trades.
Solve & review
Get updated values of lift, drag and moment coefficients as it runs.
Unlock aerodynamic performance
Aerodynamics Studies Made Accurate & Easy. Any Questions 🙋♂️
Compressible flows
Stopped rotor drag
Lift, drag & moments
Transition & stability
Aerodynamic plant model
Watch eVTOL video📽️
Sports aerodynamics
L/D & static margin
Join successful customers
From startups to classrooms to established R&D teams.
- UAV & eVTOL startups needing credible aero data without a full CFD department
- Aircraft & rocket designers iterating on concepts before committing to big campaigns
- Universities & educators giving students hands‑on 3D RANS CFD on classroom PCs
- Consultants & small teams who want full‑body CFD with predictable local compute
Run your first CFD case today 🚀
Use your geometry. Get real results.
About
Dr. Patrick Hanley is the owner of Hanley Innovations. He received his Ph.D. degree in fluid dynamics from Massachusetts Institute of Technology (MIT) department of Aeronautics and Astronautics (Course XVI). Read more ..
Products
3DFoil
MultiElement Airfoils
MultiSurface Aerodynamics
Stallion 3D
VisualFoil
VisualFoil PLUS
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Telephone: (352) 653-0875