Stallion 3D: High-fidelity Aerodynamics Software


Compressible RANS CFD • Automatic grid generation • Case setup in seconds

Stallion 3D technology ⚙️ Ask a quick questions 🧐
💻 Runs on standard Windows laptops (8 cores, 16 GB RAM recommended)

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$895 USD

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1‑Year Subscription*

$2,895 USD

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Perpetual License*

$8,995 USD

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* Free technical support included. Ask about our consulting services 🧐

What you get with Stallion 3D

Same‑day aerodynamics insight from the geometry you already have.

Direct‑from‑STL workflow
  • 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
Answers in engineering language
  • 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
High‑fidelity RANS for conceptual design
  • 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
Propulsion & special effects
  • 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

From STL to insight in a single afternoon

Quick‑start tutorials to simulate aircraft, UAVs, rockets & more.

Airplane Analysis

Stallion 3D & OpenVSP
rocket aerodynamics

Rocket Aerodynamics 🚀
Export data to Paraview

Blown Wing Aerodynamics
Light aircraft analysis

Airplane Aerodynamics
UAV aerodynamics

UAV Aerodynamics
OV-10A CFD Analysis

OV‑10A CFD Tutorial

Real‑world validation

HIST (proprietary) + RANS/k‑epsilon for credible engineering results.

NACA Report No. 647

NACA 12% Wing

Experimental results from NACA Report No. 647. Comparisons of CL & CD vs. AoA show good agreement for the NACA 0012 wing.

NASA_Technical_Paper_2772

Cessna 210

Experiment results from NASA Technical Report 2772. Comparisons of CL vs. CD, shows good agreement for the Cessna 210.

ONERA M6 Wing CFD

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 CFD Analysis

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💰

1

Import geometry

Read in your aircraft design from OpenVSP or CAD (STL file).

2

Set conditions

Set speed, AoA, sideslip, altitude and simulation resolution.

3

Auto grid

Generate the volume grid automatically for repeatable trades.

4

Solve & review

Get updated values of lift, drag and moment coefficients as it runs.

Applications gallery

Aerodynamics Studies Made Accurate & Easy. Any Questions 🙋‍♂️

propwash aerodynamics

Aircraft with propwash

small drone aerodynamics

Small drone aerodynamics

Vans RV-12 Aerodynamics

Airplane performance

Raven SWFT eVTOL Concept

eVTOL verification

winged uav

UAV endurance

eVTOL aerodynamics

Watch eVTOL video📽️

canard aerodynamics

Canard effects

Joined wing aerodynamics

Joined wing L/D

STL from OpenVSP & most CAD software

Who uses Stallion 3D?

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
NASA
Stavatti Aerospace
Middle Tennessee State University
Navmar

Run your first CFD case today 🚀

Use your geometry. Get real results.

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