CORDIS provides links to public deliverables and publications of HORIZON projects.
Links to deliverables and publications from FP7 projects, as well as links to some specific result types such as dataset and software, are dynamically retrieved from OpenAIRE .
Exploitable results
The strategic objective of the EUROSUP project was to contribute to the improvement of the competitive position of Europe as a partner in a potential future supersonic transport aircraft programme. The aim of the project was to demonstrate and assess the application of advanced aerodynamic technology to a representative second-generation supersonic transport configuration. In particular, means of reducing the drag due to shock waves and lift were investigated. Challenging target values for lift / drag (L/D) for three aircraft design points, over-sea cruise (M = 2.0, L/D>10), over-land cruise (M = 0.95, L/D>15) and take-off climb out / landing approach (L/D>8), were achieved. These targets for aerodynamic performance represent improvements of between 20% and 30% relative to the performance of first generation supersonic transport aircraft. Thus the research project is a very significant first step towards a second-generation supersonic transport that would be economically viable and environmentally acceptable.
Four major activities were completed in the project:
-CFD methods were evaluated for the aerodynamic analysis and design of a supersonic transport configuration through comparison with experimental data for drag.
-Aerodynamic design methods were evaluated for the optimisation of variants of a single wing shape to meet the three design points.
-A wind-tunnel model incorporating the aerodynamic designs was manufactured and tested at supersonic, transonic, and take-off and landing conditions.
-The aircraft model and flight vehicle configurations were analysed using CFD methods, and the results compared with the design predictions and wind-tunnel model measurements.
It was concluded that:
-The initial evaluation of CFD tools showed good prediction accuracy for supersonic cruise, moderate accuracy for transonic cruise but relatively poor accuracy for low speed.
-The application of aerodynamic design tools at high speed showed good performance by a linear theory method for supersonic design. The direct optimisation Euler methods produced a dual-point transonic/supersonic wing design that met the L/D targets. A large increment in transonic L/D was obtained, without compromising the supersonic L/D, by optimising the deflection angles for high-lift devices. The role for inverse design methods in SCT wing design was unclear. The limited evaluation showed no gains from application to wing LE profile shaping. At low speed a semi-empirical design procedure produced a wing design that met the L/D target, however there was poor modelling of the flow physics and no appreciation of design sensitivities could be obtained.
-The aerodynamic performance predicted in design was confirmed by wind-tunnel model tests at subsonic, transonic and supersonic speeds, and by independent CFD analyses. The CFD analyses gave very good agreement with the wind-tunnel results. Predictions of the increments in aerodynamic performance due to scale effect and the geometric change from model to full-scale aircraft showed that the target values for L/D would be achieved.
-No satisfactory computational procedure was found for low-speed design. Further research was therefore recommended to investigate the low-speed flows and define a design method.
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