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- Altheimer, A., et al.
(author)
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Boosted objects and jet substructure at the LHC. Report of BOOST2012, held at IFIC Valencia, 23rd-27th of July 2012
- 2014
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In: European Physical Journal C. Particles and Fields. - : Springer Science and Business Media LLC. - 1434-6044. ; 74:3
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Journal article (peer-reviewed)abstract
- This report of the BOOST2012 workshop presents the results of four working groups that studied key aspects of jet substructure. We discuss the potential of first-principle QCD calculations to yield a precise description of the substructure of jets and study the accuracy of state-of-the-art Monte Carlo tools. Limitations of the experiments' ability to resolve substructure are evaluated, with a focus on the impact of additional (pile-up) proton proton collisions on jet substructure performance in future LHC operating scenarios. A final section summarizes the lessons learnt from jet substructure analyses in searches for new physics in the production of boosted top quarks.
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- Da Ronch, A., et al.
(author)
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A framework for constrained control allocation using CFD-based tabular data
- 2011
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In: AIAA Aerosp. Sci. Meet. Incl. New Horiz. Forum Aerosp. Expos.. - Reston, Virigina : American Institute of Aeronautics and Astronautics. - 9781600869501
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Conference paper (peer-reviewed)abstract
- This paper describes a framework for control allocation problem using Computational Fluid Dynamics (CFD) aerodata, which is represented by a multidimensional array of dimensionless coefficients of aerodynamic forces and moments, stored as a function of the state vector and control-surface deflections. The challenges addressed are, first, the control surface treatment for the automated generation of aerodata using CFD and, second, sampling and data fusion to allow the timely calculation of large data tables. In this framework, the generation of aerodynamic tables is described based on an efficient sampling/data fusion approach. Also, the treatment of aerodynamics of control surfaces is being addressed for three flow solvers: TORNADO, a vortex-lattice method, and two CFD codes, EDGE from the Swedis Defence Agency and PMB from the University of Liverpool. In TORNADO, the vortex points located at the trailing edge of the flaps are rotated around the hinge line to simulate the deflected surfaces. The transpiration boundary conditions approach is used for modeling moving flaps in EDGE, whereas, the surface deflection is achieved using mode shapes in PMB. The test cases used to illustrate the approaches is the Ranger 2000 fighter trainer and a reduced geometry description of Boeing 747-100. Data tables are then generated for the state vector and multiple control surface deflections. The look-up table aerodata are then used to resolve the control allocation problem under the constraint that each surface has an upper and lower limit of deflection angle.
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| 8. |
- Da Ronch, A., et al.
(author)
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Benchmarking ceasiom software to predict flight control and flying qualities of the B-747
- 2010
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In: 27th Congress of the International Council of the Aeronautical Sciences 2010, ICAS 2010. - 9781617820496 ; , s. 2906-2912
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Conference paper (peer-reviewed)abstract
- CEASIOM, the Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods, is a framework that integrates discipline-specific tools for conceptual design. At this early stage of the design it is very useful to be able to predict the flying and handling qualities of the aircraft. In order to do this for the configuration being studied, the aerodynamic database needs to be computed and coupled to the stability and control tools to carry out the analysis. This paper describes how the adaptivefidelity CFD module of CEASIOM computes the aerodynamic database of an aircraft configuration, and how that data is analyzed by the FCSDT module to determine the flying qualities and the control laws of the aircraft. The paper compares the predicted flying qualities with the flight-test data of the Boeing B747 aircraft in order to verify the goodness of the overall approach.
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| 10. |
- Eliasson, P., et al.
(author)
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Virtual aircraft design of transcruiser - Computing break points in pitch moment curve
- 2010
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In: 28th AIAA Applied Aerodynamics Conference. - Reston, Virigina : American Institute of Aeronautics and Astronautics (AIAA). ; , s. 2010-4366-
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Conference paper (peer-reviewed)abstract
- The SimSAC project has developed the design software CEASIOM, a framework tool that integrates discipline-specific tools like CAD & grid generation, CFD, stability & control analysis etc. for the purpose of aircraft conceptual design. Significant features developed and integrated in CEASIOM are geometry, aerodynamics, flight dynamics and aeroelasticity modules. The design begins with a design specification and uses conventional design methods to prescribe a baseline configuration. Then CEASIOM improves upon this baseline by analyzing its flying and handling qualities. This paper reports on the Transonic cruiser TCR from baseline design to Tier-I design. The baseline T-tail design is based on the design specification, which is a fairly non-complicated one with the exception for the design cruise speed of Mach 0.97. The flight dynamical analysis in CEASIOM of this configuration showed that trimming the aircraft required too large deflections in the design point so a new approach with a canard configuration was designed. A model of this configuration was built and tested in wind tunnel. The paper focuses on the validation of computational tools of different fidelity, from Tier I to Tier II RANS solvers, with test data to get a range of fidelity of the tools. The results showed that Tier I methods fail to reproduce experimental pitch moment already at moderate angles of attack. Euler methods give reasonably accurate predictions but only RANS offers good overall experimental agreement for all angles attack, in particular at higher angles where the flow starts to separate.
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