The American Institute of Aeronautics and Astronautics Science and Technology Forum and Exposition 2019 (AIAA SciTech) is taking place, 7th - 11th January 2-19 at the Manchester Grand Hyatt in San Diego.
The AIAA SciTech 2019 annual forum aims to tackle the most pressing issues impacting the future of aerospace and present innovative research and technologies that offer solutions. The forum boasts over 4,000 participants from almost 1,300 institutions globally, 11 conferences across the 4 days and more than 2,000 technical papers reporting the latest innovations in aerospace.
The Centre for Modelling & Simulation (CFMS) is excited to announce that our CFD Engineer, Andrei Cimpoeru, has had two abstracts accepted by the AIAA, for the AIAA SciTech 2019. The first is focused on ‘Detached Eddy Simulation of the Flow Past 30P30N High-Lift Configuration Using High Order Discontinuous Galerkin.’ The second focused on ‘Near-Field Acoustic Predictions for Transonic Cavity Flows Through Detached Eddy Simulations in a Discontinuous Galerkin Framework’. Please see below for the full abstracts.
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Detached Eddy Simulation Of The Flow Past 30P30N High-Lift Configuration Using High Order Discontinuous Galerkin
Andrei Cimpoeru∗ CFMS, Emersons Green, Bristol, BS16 7FR, United Kingdom
Mark Allan†, Jamil Appa‡, David Standingford‡ Zenotech Ltd, Emersons Green, Bristol, BS16 7FR, United Kingdom
In order to support increased demand and increasingly strict environmental constraints, the aerospace sector has to produce quieter and more efficient aeroplane using tools from concept to final design. Airframe noise corresponds to the acoustic radiation due to turbulent flow in the proximity of aircraft components, such as, high-lift configurations and undercarriage during take-off and landing. Most of the current industrial CFD tools rely on low order methods (methods for which spatial order of accuracy is less than three). Nowadays, these methods are used in conjunction with RANS to deliver design guidance solutions for complex configurations on several millions of cells running on typical HPC clusters in a few hours. Moreover, second order methods are lacking in predicting massively separated unsteady turbulent flows due to being too dissipative. This could be an issue when investigating aero-acoustic problems with LES (Large Eddy Simulation) where waves must be tracked for long distances. Recent advances in numerical discretization schemes have proven High Order methods to be successful in tackling some of these issues. In this work, flow predictions will be presented on the 30P30N three-element high-lift configuration which was successfully tested in the wind tunnel by JAXA and FSU and used for validation and benchmarking during the third and fourth BANC (Benchmark Problems for Airframe and Noise Computations) workshops. The computations are performed using DES in a High Order Discontinuous Galerkin framework implemented in the commercial flow solver zCFD. This has been validated and compared against modern benchmarks from the 5th High Order Workshop for accuracy and performance.
Near-Field acoustic predictions for transonic cavity flows through Detached Eddy Simulations in a Discontinuous Galerkin framework
Andrei Cimpoeru∗ and Alfonsina Esposito∗ CFMS, Emersons Green, Bristol, BS16 7FR, United Kingdom
Mark Allan,† Jamil Appa, ‡ David Standingford‡ Zenotech Ltd, Emersons Green, Bristol, BS16 7FR, United Kingdom
High speed flows over open cavities are considered to be benchmark problems in Computational Aeroacoustics, as they encompass both broadband acoustic fluctuations, as well as discrete narrowband modes. Direct aerospace applications are landing gear wells and/or weapon bays that require mid-flight deployment. Modal analysis results will be presented on the ARA 2D cavity model tested in the Z4 transonic wind tunnel at Aircraft Research Association, Bedford, UK. Near-field noise predictions were performed with the SST-DES framework using high order Discontinuous Galerkin-Flux Reconstruction discretisation scheme implemented in the commercial solver zCFD. The numerical results are compared against the wind tunnel data.