AIRCRAFT MODELLING AND PERFORMANCE PREDICTION SOFTWARE
Trade Studies and Optimisation
Unusual designs and multiple configurations can be assessed simultaneously with the J2 Universal Tool-Kit with all the results instantaneously compared to the core design.
This gives you great flexibility to rapidly investigate multiple designs and compare them at the same time.
Click here to read about Optimising a Design with the J2 Universal Tool-Kit
When developing an aircraft concept, or performing sizing studies, and the ability to be able to compare all results through a single mouse click can provide a major advantage in understanding the overall design. This means that the impact of any design change on the performance and handling of the aircraft can be considered prior to committing to a solution.
The built in delta models found within J2 BUILDER can also be used to assess the sensitivity of the design to data errors or design changes. This allows the design team to direct their efforts to the points at which the aircraft is most sensitive to change and efficiently develop the optimum configuration.
Example
In the example shown here an unusual tandem wing UAV was modelled using J2 BUILDER from simple analytical data, and mass distribution of known equipment. The aircraft’s total mass and inertia information was automatically calculated for any given flight regime.
The key to this design was to be able to generate as maximum positive lift from both the wing and the horizontal tail to enable the aircraft to fly as slow as possible. As such it alternative airfoil sections were investigated.
Using the basic design, 3 deltas were created in J2 BUILDER that only required different characteristics for the airfoils under investigation to be entered. All other information for the models was referenced back to the core design.
Steady state analysis was then run for all 4 options across a series of airspeeds using J2 FREEDOM. The results for all cases were cross-plotted in J2 VISUALIZE for comparison. From here it was easy to establish the optimal airfoil section to achieve the desired design goal.
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