Aerodynamic Modeling Software
An aerodynamics tool for modeling and analyzing aircraft, propellers, high-lift devices and jet engine effects.
FlightStream® is a high fidelity aerodynamics tool perfectly suited for aircraft designers. The integrated meshing tool allows users to easily apply a surface mesh to their CAD models. The unique vorticity based flow solver, which uses only a surface mesh, produces accurate solutions in a fraction of the time required by full volume mesh CFD solvers. The solver is capable of modeling and analyzing aircraft, propellers, high-lift devices and jet engine effects. The intuitive user interface, utility of the meshing tool and robustness of the flow solver allow users of all skill levels to quickly and easily obtain accurate aerodynamic results.
FlightStream® has its CAD library and meshing tools developed in-house (no third-party meshing tools needed) where Parasolid or IGES files can be imported. FlightStream® can export geometry to STL, Wavefront Object (.obj), Standford Polygon (.ply) or TRI files.
FlightStream® uses surface vorticity sheets and vorticity-based loads that are substantially faster with convergence on the loads and does not need potential sources to make the boundary conditions work. FlightStream® users do not have to come up with combination choices of sources and doublets to get a solution.
FlightStream® uses surface vorticity sheets and vorticity-based loads whereas other traditional codes use surface pressure based loads and source-doublet combinations.
What Makes FlightStream® Unique?
FlightStream® is a unique aerodynamics tool with many advantages over traditional CFD and panel codes.
Fast & Simple Work Flow
Accurate and reliable results are the foundation of FlightStream’s development. To ensure accuracy and reliability, extensive validation has been performed using peer reviewed wind tunnel data. Comparing FlightStream® results with experimental data for all types of configurations and flight conditions has successfully validated its solutions. Below the validation is given for the Cessna 210 and NASA E.E.T. AR-12.
Lift Curve Validation
Drag Polar Validation
Complex Modeling Applications
High-Lift Devices such as flaps, slats, spoilers, etc. can be modelled in FlightStream® to analyze how the flow over the wing interacts with these complex geometries.
Finite Element Analysis
FlightStream® allows the structural analysis engineer to quickly evaluate fluid interaction effects, by generating pressure forces and mapping load distributions and moments.
Jet Engine Effects
Jet Engine Effects can be modelled in FlightStream® without a structured volume mesh, which saves valuable time when it comes to analyzing this complicated flow problem.
Propellers can be modelled in steady and unsteady flow. For steady flow, the propellers are modeled as actuator disks to simplify the analysis. All that is required are the operating characteristics of the propeller (e.g. thrust, power and RPM). In unsteady flow, propellers are modeled as rotating wings, which accurately captures the interactions between the propellers, wings and bodies. Below you can see the propeller modeling landscape in FlightStream®.
If the CHM file is located on a network location (not on the local computer), the file may open up blank. This can be fixed with the following steps:
- Run Regedit.
- Open or create (if it does not exists) the key:
- In the new key, add a new DWORD subkey named MaxAllowedZone and set one of the following values there (a value of 1 allows it to open from a network location):
0 – My Computer
1 – Local Intranet
Support Documents & Downloads
Software License Pricing
Purchase includes CD, WibuKey and 12 Months Software Maintenance. Floating and Node Locked Licenses. Student License Pricing
DARcorporation uses Wibu-Systems WibuKey copy protection for the FlightStream® licensing. The WibuKey concept consists of a WibuBox and the Wibu software. The WibuBox or WibuKey refers to the USB dongle that contains the software license. Our software needs the license to be present so that it will run. The Wibu software (or drivers) refers to the Wibu program that must be installed so that the computer can recognize WibuBoxes.
FLOATING LICENSE: Software is accessible from multiple computers, but limited to the number of licenses purchased. The WibuKey does not need to be attached to the local computer where FlightStream® starts. All computers running FlightStream® must be able to access the license server.
NODE LOCKED LICENSE: (and using Floating License as Node Locked License): Follow installation instructions for floating license except that the WibuKey must be attached to the local computer where FlightStream® starts. Software then can be used on the computer the software is installed on.
- OS: Windows (64 bit) 7 and up
- Free Hard-Disk Space: 100 MB (More space is required to save simulations)
- RAM: 2-6 GB
- Dual-core processors or better
- Dedicated graphics card
- OS: Windows 7, 10 (64 Bit)
- Free Hard-Disk Space: 1 GB (More space may be required to save large simulations)
- RAM: 6-16 GB (Higher memory may be needed for large simulations)
- Quad-core processors or higher for parallel scaling of the solver
- Dedicated graphics hardware that has 3D capability, z-buffer etc.. Integrated graphics chipsets are not recommended.
- Weight & Balance Estimation with Automated Structural Analysis for Subscale Flight Models, TU Delft Master Thesis, L. de Ruiter, Delft University of Technology, Delft, The Netherlands; October 2020
- Vertical Tail Reduction Through Differential Thrust, TU Delft Master Thesis, J. Soikkeli, Delft University of Technology, Delft, The Netherlands; March 2020
- Highly Non-Planar Aircraft Configurations: Estimation of Flight Mechanical Derivatives Using Low-Order Methods, DLRK 2019, J. Quitter, M. Marino, J. Bauschat, RMIT, Melbourne, Australia; 2019
- Modeling Boundary Layer Ingestion at the Conceptual Level, ISABE-2017-22700, A. Turnbull, H. Jouan, P. Giannakakis, A.T. Isikveren, Safran Tech; 2017
- Energy-Based Sizing and Mission Performance Analysis Approach for Novel Flight Vehicle Concepts, AIAA-2019-2801, I. Chakraborty, R. Hartfield, Auburn University, Auburn, AL; V. Ahuja, Research in Flight, Auburn, AL; June 2019
- Aero-Propulsive Analysis for Contemporary Conceptual Design, AIAA-2019-3019, V. Ahuja, Research in Flight, Auburn, AL; I. Chakraborty, R. Hartfield, Auburn University, Auburn, AL; June 2019
- Development of a Modeling, Flight Simulation, and Control Analysis Capability for Novel Vehicle Configurations, AIAA-2019-3112, I. Chakraborty, Auburn University, Auburn, AL; V. Ahuja, Research in Flight, Auburn, AL; A. Comer, O. Mulekar, Auburn University, Auburn, AL; June 2019