scholarly journals Large-scale parallel unstructured mesh computations for 3D high-lift analysis

1999 ◽  
Author(s):  
D. Mavriplis ◽  
S. Pirzadeh
Keyword(s):  
Large Scale ◽  
Unstructured Mesh ◽  
High Lift

Summary of JAXA Studies for the 2nd AIAA CFD High Lift Prediction Workshop Using Structured and Unstructured Mesh CFD

2014 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Kazuomi Yamamoto ◽  
Yasushi Ito ◽  
Tohru Hirai ◽  
Kentaro Tanaka
Keyword(s):  
Unstructured Mesh ◽  
High Lift

Validation of Computations Around High-Lift Configurations by Structured- and Unstructured-Mesh

2006 ◽  
Vol 43 (2) ◽  
pp. 395-406 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Kazuomi Yamamoto ◽  
Kunihiko Kobayashi
Keyword(s):  
Unstructured Mesh ◽  
High Lift

Design of a Large-Scale High-Lift Morphing A320 Wing Based on Electro-Mechanical Actuators and Shape Memory Alloys

2019 ◽  
Author(s):  
Yannick T. Bmegaptche Tekap ◽  
Alexandre Giraud ◽  
Gurvan Jodin ◽  
Clément Nadal ◽  
Abderahmane Marouf ◽  
...  
Keyword(s):  
Shape Memory Alloys ◽  
Shape Memory ◽  
Large Scale ◽  
High Lift

CFD-CAA Validation on a Large-Scale High-Lift Configuration

2016 ◽  
Author(s):  
Alexander Kolb ◽  
Roland Ewert ◽  
Juergen Dierke ◽  
Michael Pott-Pollenske ◽  
Alexander Buescher
Keyword(s):  
Large Scale ◽  
High Lift

Large-Scale High-Lift CAA-RPM Simulations

2014 ◽  
Author(s):  
Alexander Kolb ◽  
Alexander Buescher ◽  
Roland Ewert
Keyword(s):  
Large Scale ◽  
High Lift

scholarly journals Numerical investigation of frequency-amplitude effects of dynamic morphing for a high-lift configuration at high Reynolds number

2019 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Abderahmane Marouf ◽  
Yannick Bmegaptche Tekap ◽  
Nikolaos Simiriotis ◽  
Jean-Baptiste Tô ◽  
Jean-François Rouchon ◽  
...  
Keyword(s):  
Large Scale ◽  
Time Dependent ◽  
Navier Stokes ◽  
Simultaneous Increase ◽  
Static Case ◽  
Turbulent Structures ◽  
Trailing Edge ◽  
High Lift ◽  
Content Type ◽  
Eddy Simulation

Purpose The purpose of this study illustrates the morphing effects around a large-scale high-lift configuration of the Airbus A320 with two elements airfoil-flap in the take-off position. The flow around the airfoil-flap and the near wake are analysed in the static case and under time-dependent vibration of the flap trailing-edge known as the dynamic morphing. Design/methodology/approach Experimental results obtained in the subsonic wind tunnel S1 of Institut de Mécanique des Fluides de Toulouse of a single wing are discussed with high-fidelity numerical results obtained by using the Navier–Stokes multi-block (NSMB) code with advanced turbulent modelling able to capture the predominant instabilities and coherent structure dynamics. An explanation of the dynamic time-dependent grid deformation is provided, which is used in the NSMB code to simulate the flap’s trailing-edge deformation in the morphing configuration. Finally, power spectral density is performed to reveal the coherent wake structures and their modification because of the morphing. Findings Frequency of vibration and amplitude of deformation effects are investigated for different morphing cases. Optimal morphing regions at a specific frequency and a slight deformation were able to attenuate the predominant natural shear-layer frequency and to considerably decrease the width of the von Kármán vortices with a simultaneous increase of aerodynamic performances. Originality/value The new concept of future morphed wings is proposed for a large scale A320 prototype at the take-off position. The dynamic morphing of the flap’s trailing-edge is simulated for the first time for high-lift two-element configuration. In addition, the wake analysis performed helped to show the turbulent structures according to the organised eddy simulation model.

scholarly journals Reynolds number and wind tunnel wall effects on the flow field around a generic UHBR engine high-lift configuration

2020 ◽  
Vol 11 (4) ◽  
pp. 1009-1023 ◽  
Author(s):  
Junaid Ullah ◽  
Aleš Prachař ◽  
Miroslav Šmíd ◽  
Avraham Seifert ◽  
Vitaly Soudakov ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Flow Field ◽  
Test Section ◽  
Large Scale ◽  
Scale Model ◽  
Small Scale ◽  
Wall Effects ◽  
Tunnel Wall ◽  
High Lift

Abstract RANS simulations of a generic ultra-high bypass ratio engine high-lift configuration were conducted in three different environments. The purpose of this study is to assess small scale tests in an atmospheric closed test section wind tunnel regarding transferability to large scale tests in an open-jet wind tunnel. Special emphasis was placed on the flow field in the separation prone region downstream from the extended slat cut-out. Validation with wind tunnel test data shows an adequate agreement with CFD results. The cross-comparison of the three sets of simulations allowed to identify the effects of the Reynolds number and the wind tunnel walls on the flow field separately. The simulations reveal significant blockage effects and corner flow separation induced by the test section walls. By comparison, the Reynolds number effects are negligible. A decrease of the incidence angle for the small scale model allows to successfully reproduce the flow field of the large scale model despite severe wind tunnel wall effects.

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