|Multi-disciplinary design approaches and performance assessment of future combat aircraft|
|Applied Vehicle Technology|
Aircraft Design, CFD, Control Devices, Delta Wing, Dynamic Maneuver, Flight Performance, Low Observability, Propulsion Concept, Signature, Stability and Control, Structural Design, Vortex Flow
The prediction of vortical flowfields, as well as the resulting static and dynamic aerodynamic behavior of delta wings and highly agile aerial vehicle configurations, has been the subject of several AVT activities over the past 10 years. In AVT-080, AVT-113 and AVT-183, flow physics prediction with high fidelity CFD methods and comparisons to experimental data for delta wing aerodynamic flow phenomena have been in the focus. Flow phenomena, such as vortex breakdown, flow separation on sharp and round leading edges and flow separation due to highly swept wings have been studied extensively.
The investigations regarding prediction capabilities have been extended within these Task Groups and follow-on activities to real applications, like the F16XL CAWAPI, X-31 and a generic NATO AVT combat aerial configuration called “SACCON”. These follow-on activities took place in Task Groups AVT-161 and AVT-201, the Specialists’ Meeting AVT-189 – all on “Stability and Control Prediction Methods for NATO Air Vehicles”. These last three activities did not only focus on the flow physics prediction, but also on the overall aerodynamic behavior, dynamic derivatives prediction and the layout and assessment of control devices with respect to the entire flight envelope covering multiple flow regimes. In AVT-251, finally, the prediction methods are used to design an effective, agile aerial vehicle consolidating several design aspects in addition to aerodynamics.
A couple of design aspects are covered in AVT Task Groups as follows:
• AVT-232 is dealing with the prediction and assessment of infrared signature.
• AVT-233 is dealing with aeroacoustics of Engine/Rotor installation for Military Air Vehicles and is also investigating acustic shielding effects.
• AVT-239 is dealing with new innovative control effectors.
All these activities use high fidelity computational methods to define and to understand the areas of interest. Furthermore, they all have in common the goal to achieve an enhanced prediction capability to assess the performance of future NATO aerial vehicles.
Over the last ten years a remarkable group of specialists with high expertise in these fields worked together under the NATO STO/AVT sponsorship and established an outstanding knowledge base. The purpose of the RSM is to bring together experts from the NATO community in order to present and discuss the results achieved so far and to provide new aspects to the overall NATO and AVT community.
The objective of the RSM is to bring together a spectrum of design aspects and overall design experiences for effective, agile NATO aerial vehicles.
The goal is to demonstrate the performance of existing design methods with respect to applicability and reliability. Requirements for further design and design method developments should be discussed as well as design strategies using advanced design tools like multi-fidelity methods or reduced order modeling (ROM).
• Preliminary and conceptional design of military effective, agile aircraft.
• Aerodynamic design using CFD and Multi-Fidelity methods
• Control device and control concept design
• Engine design and integration
• Structure design and aeroelastic assessment
• Signature evaluation and design concepts
• Flight mechanics analyses and control systems