Stallion 3D: Aerodynamics Simulation Software
Validate aerodynamic designs quickly & accurately on Windows 11, 10 & 7.
Stallion 3D was specifically developed to validate complex aerodynamic designs using high fidelity RANS CFD simulations. It fills the gaps between low accuracy vorticity flow solvers and expensive HPC & cloud based CFD software. Stallion 3D imports your actual design and automatically generates the volume grid for a quick and accurate RANS analysis. Stallion 3D is the only aerodynamic software tool that has the speed and fidelity required to ensure your success. Watch above video for a quick overview đē
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Stallion 3D is your complete 3D Aerodynamics Solution
No need to purchase expensive add-ons for gridding or graphics.
Pre-processing (Built-in):
- Stallion 3D inputs a STL file of your design
- Grid generation is completely automatic (just click the menu)
- Stallion 3D analyzes the actual geometry and you do not have to defeature your design.
CFD Solvers (Built-in)
- Stallion 3D accurately solves the Reynolds Averaged Navier-Stokes Equations for air or water flows analysis
- The k-epsilon turbulent model is used for realistic flow simulation at any angle of attack (0 to 360 degrees) and any cross flow angle (0 to 360 degrees)
- Stallion 3D also has a Laminar Navier-Stokes solver
- Stallion 3D also has a 3D Compressible Euler solver
- The flow solvers use a 4-stage Runge-Kutta time marching scheme
- A flux vector splitting scheme is used for shock capturing and to work out the domain of dependence
- Actuator discs (up to 100) are used to model jet, prop wash and other propulsion effects (available in the RANS solver)
- Quasi-steady surface rotations (in any direction and frequency) to compute stability derivatives and other special flow effects (e.g. a rotating sphere or cylinder).
Post Processing (Built-in).
- Reports of CL, CD, CM, and related forces and moments coefficients in the coordinates directions
- Reports of lift, drag, yaw, roll, pitch magnitudes and related forces and moments in the coordinates direction
- Plots of pressure, Mach number, velocity, density and temperature on the STL surfaces as a contour color plot
- Plots of pressure, Mach number, velocity, density and temperature at constant coordinate slices in the flow field
- Plots of 2D line graphs of Cp, velocity, mach number, density and temperature at constant coordinates locations long the STL surface (for example, you can plot Cp (x) at any span location along the wing)
- Graphs of streamlines (originating at any location in the flow) using arbitrary colors or using colors designated by the local flow pressure, velocity, density, temperature or Mach number
Even More Benefits!
- SameDayCFD: Fast Multiple Core CFD Analysis on Your MS Windows Laptop or Desktop.
- Install and Run Stallion 3D on Any of Your Computers Using the Same Password.
- No Hidden Cloud Costs! All Computations are Performed & Stored on Your Computer.
Pre-processing (Built-in):
- Stallion 3D inputs a STL file of your design
- Grid generation is completely automatic (just click the menu)
- Stallion 3D analyzes the actual geometry and you do not have to defeature your design.
CFD Solvers (Built-in)
- Stallion 3D accurately solves the Reynolds Averaged Navier-Stokes Equations for air or water flows analysis
- The k-epsilon turbulent model is used for realistic flow simulation at any angle of attack (0 to 360 degrees) and any cross flow angle (0 to 360 degrees)
- Stallion 3D also has a Laminar Navier-Stokes solver
- Stallion 3D also has a 3D Compressible Euler solver
- The flow solvers use a 4-stage Runge-Kutta time marching scheme
- A flux vector splitting scheme is used for shock capturing and to work out the domain of dependence
- Actuator discs (up to 100) are used to model jet, prop wash and other propulsion effects (available in the RANS solver)
- Quasi-steady surface rotations (in any direction and frequency) to compute stability derivatives and other special flow effects (e.g. a rotating sphere or cylinder).
Post Processing (Built-in).
- Reports of CL, CD, CM, and related forces and moments coefficients in the coordinates directions
- Reports of lift, drag, yaw, roll, pitch magnitudes and related forces and moments in the coordinates direction
- Plots of pressure, Mach number, velocity, density and temperature on the STL surfaces as a contour color plot
- Plots of pressure, Mach number, velocity, density and temperature at constant coordinate slices in the flow field
- Plots of 2D line graphs of Cp, velocity, mach number, density and temperature at constant coordinates locations long the STL surface (for example, you can plot Cp (x) at any span location along the wing)
- Graphs of streamlines (originating at any location in the flow) using arbitrary colors or using colors designated by the local flow pressure, velocity, density, temperature or Mach number
Even More Benefits!
- SameDayCFD: Fast Multiple Core CFD Analysis on Your MS Windows Laptop or Desktop.
- Install and Run Stallion 3D on Any of Your Computers Using the Same Password.
- No Hidden Cloud Costs! All Computations are Performed & Stored on Your Computer.
The Stallion 3D 5.0 Work Flow: Setup in Seconds
STL file input. No Geometry De-featuring. No user grid generation!
Import the geometry
Set the flow conditions
Setup the CFD
Generate Grid/Solve Flow
Validation with Experiments
Revolutionary Algorithm, HIST, Computes Accurate Solutions
The DrivAer Experimental Model
The DrivAer experiment is a validation exercise for CFD solutions of passenger cars. The picture shows the flow velocity near the surface of the DrivAer model with mirrors and detailed under body. The problem was analyzed in Stallion 3D using 1.7 million cell and the RANS/k-epsilon solver. The solution was unsteady with an average drag coefficient of about 0.29.
HL-20 Analysis
The results from Stallion 3D 5.0 RANS solver (CL = 0.41, CD = 0.25 & CM = -0.0387 ) were compared to the findings of NASA Technical Memorandum 4117,Transonic Aerodynamic Characteristics of a Proposed Assured Crew Return Capability (ACRC) Lifting-Body Configuration by George M. Ware. From the graphs, the corresponding experimental results were (CL = 0.48, CD = 0.24 & CM = -0.042). The geometry was obtained from NASA OpenVSP. The flow parameters for this case are M = 1.2 with an angle of attack of 12 degrees. This simulation used about 480,000 cells and ran for 3 hours on a 2 GHz laptop computer.
ONERA M6 Wing
Stallion 3D used the August, 2016 implementation of its RANS/k-epsilon solver for this analysis the ONERA M-6 wing. The CAD model was obtained from NASA OpenVSP hangar. The simulation was setup for the well know case of M=0.84 and an angle of attack of 3.06 degrees. This case used a grid of 447,640 cells and ran for 6 hours on a 2 GHz laptop computer with 4 cores. The picture shows the pressure on the wing along with comparisons of the computed CP versus the experimental data at 2 stations along the wing. Since no experimental values of CL and CD were found, the lift and drag coefficients were compared to results from NASA's CFL3D (Spalart-Allmaras model).
NASA CFL3D |
Stallion 3D |
% Difference |
|
| CL | 0.2754 | 0.275 | 0.145% |
| CD_SkinFriction | 0.00567 | 0.00483 | 14.81% |
| CD_Pressure | 0.01348 | 0.014 | -3.858% |
| CD_Total | 0.01914 | 0.0188 | 1.776% |
Stallion 3D Tutorials
Follow these instructions to get started in just minutes.
How to Analyze a Cessna 182
Click here to learn the exact steps needed to analyze a Cessna 182 aircraft using Stallion 3D.
Analyze Race Car Wing
Click here to watch the exact steps needed to design and analyze a rear wing spoiler for a sports car using Stallion 3D.
How to Analyze a BWB Aircraft
Click here to learn the exact steps needed to analyze a blended wing body (BWB) using Stallion 3D.
Stallion 3D Customers
The following organizations use Stallion 3D for education, research & design.
Contact Us About Stallion 3D 5.0 With HIST
Email or telephone us with your questions or comments.
Call us at (352) 653-0875
About
Dr. Patrick Hanley is the owner of Hanley Innovations. He received his Ph.D. degree in fluid dynamics for Massachusetts Institute of Technology (MIT) department of Aeronautics and Astronautics (Course XVI). Read more ..
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