|Multi-disciplinary design and performance assessment of effective, agile NATO air vehicles
|Applied Vehicle Technology|
Aircraft Design, CFD, Control Devices, Delta Wing, Dynamic Maneuver, Flight Performance, Low Obersevebility, 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 vehicles 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 with experimental data for delta wing aerodynamic flow phenomena have been the focus. Flow phenomena such as vortex breakdown, flow separation on sharp and round leading edges, as well as flow separation due to highly swept wings have been studied extensively.
These 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 aerial configuration SACCON. These follow-on activities took place in Task Groups AVT-161 and AVT-201, as well as the Specialists’ Meeting AVT-189, all on “Stability and Control Prediction Methods for NATO Air Vehicles”. These last three activities not only focused 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 and multiple flow regimes.
All of activities applied an integrated approach between experiments from wind tunnel investigations, flight test data, and the use of high fidelity computational methods to define and understand the areas of interest. Further, they all have in common the goal to achieve an enhanced prediction capability using an integrated CFD-Experimental approach.
There are other activities currently running (or being proposed) regarding the prediction of aerodynamic flows and stability and control behavior which are a major component of the design requirements for low observable, highly agile aerial configurations:
• AVT-232 is dealing with the prediction and assessment of infra red 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.
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 RTG is to re-design a given generic aerial platform used already in AVT-161 and -201 and to demonstrate the developed multi-discilinary design approach.
The STO/AVT aerial configuration SACCON should be re-designed based on given requirements of a desired mission and/or parts of a defined flight envelope. The design should incorporate several additional design aspects and disciplines depending on the availability by the contributing nations and connections to other Task Groups.
The goal is to demonstrate the performance of the designed configuration based on the requirements of the mission definition. Finally, the design strategy and use of advanced design tools should be documented and evaluated with respect to applicability and reliability of the used approach and methods.
• Aerodynamic shape design of a given aerial vehicle plan form.
• Detailed CFD validation of static and dynamic critical aerodynamic states by use of existing experimental data
• Aerodynamics design and control device concept design
• Assessment of flight performance and S&C
• Air Intake and nozzle design
• Layout of a propulsion system
• Assessment of signature requiremente
• Structure design and aeroelasticity
• Flight mechanics behavior and control system assessment