Span-efficiency factor (aka Oswald factor) included in results (and available as objective for optimizations)
Drag-and-Drop: Aeolus ASP model files (*.xml) and CAD files (*.stp, *.obj, *.x3d) can be easily loaded through drag and drop
New result charts of Center-of-pressure and Aerodynamic-center locations
New result chart Cmy(Cl)
Results include figures on the required power and thrust for level flight at different speeds
Airfoil drop-down list is now searchable
Lift distribution plot: added the elliptical reference curve
New line force distribution view in 3d shows the strip-wise force components
Optimization-, and Parameter-study progress panels are now equipped with chart controls to zoom in/out
Improved the force balance 3d view
CAD Model import transformations sequence improved and text fields aligned with this new sequence to make it more intuitive
Aircraft reference surface changed to the sum of the reference surfaces of all wings in the model. Same with MAC, taken as the surface-weighted average.
Fixed the sign of Cdi in the span-wise distribution charts. Now, local strip-wise thrust is shown as negative Cdi
Password reset feature available in the sign-in panel
As usual: bug fixes and performance improvements
Version 4.22 available (Download) - Give it a try!
Optimization feature now uses CMA-ES algorithm by default (instead of BOBYQA) to improve convergence
Fixed issue of multiple warning messages popping up on bad number format
Improved Nacelle modeling feature
Cl(AOA) chart has a trend line
C-Wing optimization example added to the Quickstart menu
Minor bug fixes and performance improvements
For Freefly's AltaX aircraft, we have been optimizing their current blades using Aeolus ASP. The
resulting blade shape proposed by the optimizer has been machined from Aluminum and tested a few days ago.
Simulation (Aeolus ASP): 4.2%
With this good agreement between simulation and test we are now prototyping another blade that was found using Aeolus ASP promising approx. 19% efficiency
Command line/API: AeolusASP can be run from the command line. The User Manual provides more information.
Airfoil contour in Cp plots: 2D plots of chord-wise pressure coefficients are now normalized and show the airfoil contour at the current strip. Also, a data table was added
to export the plot data to any other plotting tool (right-click in the table)
Froude model: Propeller results now also include the Froude model.
The Power-Speed-Coefficient is computed for Propellers and available for Optimization or Parameter studies
Minor bugfixes of the login and licence panel.
Aeroelasticity with Aeolus ASP
Next Generation Propeller Blades: +18% endurance for UAVs?
Compared to legacy UAV props in the 33 inch range, +18% more efficient prop shapes were found using the numerical shape optimization
feature of Aeolus ASP. As we move torwards thinner airfoils and higher aspect ratio blades, aeroelasticity and manufacturing feasibility becomes increasingly challenging. We use FEM and numerical
aeroelasticity analysis based on a week coupling of Aeolus ASP and NX Nastran, providing a feedback loop between aerodynamic loads and structural displacement.
Multi-threading: Up to 32 CPU cores may now be used, enabling even faster optimizations on modern workstations. Also, we have just invested in a cluster ourselves
for future development and engineering optimization services for our clients. An additional cloud-based HPC computing option is planned for the future.
An improved surrogate model feature is now available and can be fine-tuned through a number of custom settings accessible in the Screening Tree.
Major updates on the Users Guide: Synchronized with the latest GUI, containing more information, and describing modeling, results, and
optimizations/parameter-study features in more detail.
Reynolds number analysis now also available for propeller blade analysis
Minor performance improvements
XML files for propeller blades only define the first blade, as all other blades on the hub are a copy of that blade. This simplifies scripting of XML files outside the GUI.
Update to the latest JavaFX version 17.
New example propeller APC 19x12" available through the quick start menu.
Preferences available again
Blade color selection applies to all blades on the hub
Surrogate model can handle optimization restarts and design space changes
Version 4.18 released
Improved aerodynamic solver for higher fidelity in propeller analysis based on wake model improvements, particularly for low advance ratios (e.g. hover). Check out the
comparison with wind tunnel results below:
Surface smoothing option available in the Discretization panel. When enabled, wings and propeller blades are lofted through a spline instead of the piecewise linear
interpolation resulting in a smoother surface.
Surrogate model for optimizations: You can enable the training of a surrogate model during the optimization. When the fidelity of the surrogate is good enough, the optimizer will
use the predictions from the surrogate instead of doing an exact analysis, which ultimately speeds up the optimization. Give it a try! A full documentation will come with the next release.
NACA4412 added to the default airfoil catalogue (often used on UAV propellers)
Boxwing propeller example added to the QuickStart Menu
Propeller pitch chart added
Removed constraints on propeller blade twist
Improved UX through various GUI enhancements
Licensing model: Aeolus ASP is now available with different licenses. Check out our store for more information
Optimization constraints text fields parse correctly
ANSYS export fixed
Lift coefficient sign fixed for negative AOAs
KNOWN ISSUES to be resolved with the next release:
User preferences panel not available
Quick start guide and User manual show an outdated model tree structure
On propeller blade shape optimizations: Global vs. local optimum
Specifically for propeller shape optimizations, version V4.14 sometimes runs into local optima resulting in not-so-feasible (yet interesting) results, such as this one:
The main reason is, that propeller shape optimization problems have a very high modality (that is, there are many local optima) and the global optimum is more challenging to find. If you restart
your optimization case multiple times and each time get a different result, then its a good indication that these are local optima and the optimizer struggles to find the global optimum.
To improve the optimization robustness, the algorithms in Aeolus ASP are getting tweaked at the moment. One example of improved robustness is shown below on a an eggholder test function. The left picture uses the current optimizer from Version 4.14
which exhibits limited design space exploration, whereas the right picture shows the new one to come in the next version. and which finds the global optimum
Here is a teaser for some more robust blade shape optimization in the upcoming version. Also, you can see that surface smoothing is now available :)
A place for discussions and suggestions:
We’re using GitHub Discussions as a place to connect with other members of our community. We hope that
Various GUI improvements for modeling and postprocessing
Optimization shows current best value
Optimization can be paused and restarted
At the end of the optimization the best design gets loaded
Less strict requirements for the model's XML file
Additional unit system mm-t-s (for FEM users)
CSV export feature of sections, super sections and reference points
Improved rendering of large vehicles
Fixed wrong pressure values from propeller models when exported to FEM
The property panel has been fixed such that it does not get cleared anymore when making changes that invalidate the previous results
29.09.2020 - Version 4.8 released
Quick start optimization model added, accessible through the Quick start menu
Parameter study feature more stable
Step-wise constraints working again
Blender Dialog more stable now
Airfoil import dialog works now also multiple times
Unit systems table is showing conversion factors again
17.09.2020 - Version 4.5 released
DLL loading problems resolved
Flaps table bugs resolved
FEM Export to ANSYS and NASTRAN fixed
06.09.2020 - Version 4.3 released
Graphics performance improvements through a new wireframe speed up the rendering and therefore also the wing shape optimizations
BOBYQA and CMAES Optimizer settings adapted to recent literature recommendations
Negative design lift force is now supported
Additional results in the output summary tables
Reduced Installer file size due to removed libraries
Increased app stability
Freezing Flight condition panel resolved
Optimization/Parameter study panel maintains constraint settings also after restart
20.01.2020 - Version 4.2 released
in the Geometry tab: The Table is now editable again
The NASTRAN Export method works again
12.01.2020 - Version 4.1 released
Happy new year - Aeolus ASP is now free and does not require any licence :)
NEW FEATURE: Propeller blade analysis
It is now possible to review the flow characteristics on a rotating propeller. It can have any number of blades and can be operating as compressor or turbine (eg for wind energy).
Validation has been done against wind tunnel data.
To access the feature, just load the default propeller from the Quick-Start menu and modify as needed.
Switched to JavaFX to improve graphics on 4k monitors and to resolve reported graphic issues with some graphic cards.
05.03.2019 - Version 4.0 released
NEW FEATURE: Propellers
Arbitrary number of propellers can be added to the model. Each propeller has a thrust vector which adds to the aircraft force balance and enables to study different propeller configurations,
such as positions, mount angles, and thrust.
Additional result parameters related to propulsion, such as rate of climb, and pitch angle.
Additional 3d plot entities: Center of gravity location, force balance, flight path angle, and horizontal reference
NEW FEATURE: Unit system
The systems of units can now be selected. Available systems are SI and Foot-pound-second (FPS). The system of units is saved with the model.
New formulation of penalties delivers much better results and helps the user to identify which constraints are violated. Also, the standard penalties have been changed and allow for a more
Improved optimization history plot showing the objective function including all penalties
Additional constraints are now available: Pressure coefficient, geometry change rates, pitch angle, flight path angle, rate of climb, center of gravity location
Improved labels in 3d view
Bugfix in C_l_wet constraint. The lift coefficient of a strip does now take into account the full component of the force perpendicular to the onset flow, not only the part projected into the
x-z-plane. Optimizations using this constraint now run much more robust and deliver better results.
Update of third-party libraries and the runtime environment for improved performance.
Improved exception handling
28.01.2019 - Version 3.11 released
NEW FEATURE: First propulsion parameters (Engines and Propeller feature to come soon)
Additional plots for required thrust and performance as function of airspeed at a given altitude for steady horizontal flight.
Thrust and performance parameters are accessible as objective functions, and constraints for optimization and parameter studies
Default penalty factors improved for different optimization constraints.
Increased resolution of carpet plots.
Default viscous drag coefficient changed to a more typical value, which can be used for most cases (at Reynolds numbers greater than 200 000)
04.01.2019 - Version 3.10 released
NEW FEATURE: Model export to CAD
Allows easy geometry export to all major CAD systems, including CATIA, SolidWorks, NX and many more using the STL format.
Undo/Redo bug fixed
Additional constraints are available in the optimization. In particular, structural constraints on the root bending now enable the analysis of bell-shaped lift distributions and
new configurations with proverse yaw.
Notification when updates are available
Updated libraries increase performance
18.11.2018 - Version 3.9 released
Additional licence types are available, now also including a Free licence.
Updated in-app links to tutorials, store, and downloads due to a new website structure
Bugfix in airfoil import dialog
Values of design variables are shown as real values, not normalized
09.11.2018 - Version 3.8 released
Additional User hints in case of inconsistent bounds of design variables
2D pressure distribution plots include the y position of the current strip
03.11.2018 - Version 3.7 released
NEW FEATURE: Parameter studies feature
Enables automatic screening of parameters and the impact on specific results. For example, this feature can be used to understand the change of the static margin due to a change of the
Parameters include real and integer values, including geometry, discretization, computation settings etc.
Internal checks make sure that the setup is consistent
An additional results node provides access to the screening results. This is also true for optimizations.
Multiple parameters can be screened at the same time
More objective functions available
Design variables now also include flap angles
Number of panels per strip need not be even but may also be odd.
Strip-wise refinement option BOTH added. This increases the panel density at both extremities of a strip.
Different options for the definition of a section's chord length.
Coordinates do not need to be normalized anymore.
The model can also be loaded when the required airfoil is not available in the airfoil catalog. In this case a dummy airfoil will be used (NACA0012)
The airfoil name is not case-sensitive in the xml file
Names may contain dots
Preferences dialog enables the definition of colors, sizes, arrow types etc.
User Settings are saved when closing the application and restored at the next start.
Freshwater and Seawater models load properly
Improved Error Handling allows to save the model before potential crash
Multi-threading accelerates start-up
White canvas background and larger font size
Improved result plots of strictly vertical wings (such as VTPs)
xml suffix removed from model name
Automatic logging of results in a text file
New aileron example accessible through the QuickStart menu
Additional checks and error messages when loading an xml file improve debugging of manually created xml files
23.09.2018 - Version 3.6 released
NEW FEATURE: Flaps
Each airfoil provides an optional flap to easily model ailerons, elevons etc.
More robust error handling at start-up
Open File- dialog working properly when invoked multiple times
Anonymous bug reports can be sent
Improved modelling of vertical wings (such as VTPs)
New performance plot Lift/Drag as a function of speed and altitude
15.09.2018 - Version 3.5 released
Added over 1000 airfoils to the built-in airfoil catalog
Airfoil import feature allows easy import of multiple airfoil files at the same time.
All airfoils in the catalog are accessible for inspection through a node in the Model Tree
02.09.2018 - Version 3.4 released
new Fluids available (Seawater and Freshwater)
definition of additional fluid parameters
2D plot of the lift coefficient and Mach number as a function of speed and altitude
Less strict format requirements allow different number formats, comment sections and different separators. As result, it is more compatible with the traditional online database formats
and enable direct import without a need to tweak the airfoil files by hand.
Improved control of panel density through strip-wise definition of density and distribution.
Minor bug fixes and other improvements
21.08.2018 - Version 3.3.1 released
Third-party libraries updated for stability and performance
Improved Windows Installer
12.08.2018 - Version 3.3 released
Easy access to the Quick-Start and User Guide, tutorials, and examples
through a Welcome Dialog at start-up, and a new QuickStart menu item
08.07.18 - Version 3.2 released
Licence check shows warning message when there is no internet connection.
03.06.2018 - Version 3.1 released
Nacelle feature stable
Toolbar icons path repaired
02.06.2018 - Version 3.0 released
NEW FEATURE: Multiple wings
Additional wings can be added to the model, such as tail planes, split flaps, biplanes, etc.
Unlimited number of additional, generic wings
All parameters of all wings are also accessible in the optimization
Individual wing designations and colors easy modelling
NEW FEATURE: Additional 3D plots
Surface velocity vectors
Center of pressure location
Aerodynamic center location
Global angle of attack
Reynolds number (strip-wise)
NEW FEATURE: Nacelle
Easy modelling of circular wings, such as engine nacelles or ring wings
Polar plot and aerodynamic coefficients of all wings, and of the entire aircraft, respectively.
Oswald factor added
Parameter designations improved
Tapered blends for twist and chord using different options (Const.,Linear,Sin,1-Cos)
Panel includes estimated memory requirement
Large models do not throw warnings anymore
Constraint violation penalty sign corresponds to goal type
Sweep variation in blends
And some more minor improvements
Geometry panel shows the Wing's dependent parameters, such as wing area and mean aerodynamic chord
Model tree structure improved
Additional model checks including penetration of symmetry plane
New optimization algorithm CMA-ES implemented
Reference system node removed. The default reference area is the projected wing area and the reference length is the mean aerodynamic chord
Kernel update for improved stability and performance
25.03.2018 - Version 2.5 released
Blending dihedral changes (e.g. for smooth transitions to winglets)
Undo and Redo buttons available in the toolbar
Solver selects Kernel according to Windows version
Numbered sections improve modelling
12.02.2018 - Version 2.4 released
NEW FEATURE: Constrained optimization
Constraints can be defined to avoid unfeasible designs. Available constraints include stability measures and the local lift coefficient.
Optimization algorithm BOBYQA improved
31.01.2018 - Version 2.3 released
This is the initial release of Aeolus Aero Sketch Pad.