Numerical Maximum Lift Predictions of a Realistic Commercial Aircraft in Landing Configuration

Bier, Niko; Rohlmann, David; Rudnik, Ralf

doi:10.2514/6.2012-279

Cited by 17 publications

(4 citation statements)

References 17 publications

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“…Within this project, numerical and experimental investigations with detailed models of an Airbus A320 and large-scale flight tests have been performed, to improve the prediction of the aerodynamic performance at maximum lift. However, the prediction of the aerodynamic effects at maximum lift including the behavior of the vortex system with numerical methods is still a challenging task [10]. Similar findings derive from the NASA High-lift prediction workshop.…”

Section: Introductionmentioning

confidence: 63%

Numerical simulations of streamwise vortices on a high-lift wing

Landa

Radespiel

Wild³

2016

CEAS Aeronaut J

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This contribution presents results of numerical simulations on a generic high-lift configuration. Properties of the computational grid are briefly described. The numerical simulations are performed with the DLR-TAU-Code at different angles of attack up to stall. The Menter-SST eddy viscosity turbulence model and the JHh-v2 Reynolds-Stress-Model are applied. Streamwise vortices arise at the edge of a slat, which is cut off in spanwise direction, and the corresponding edge of the clean nose. These vortices interact with the flow along the suction side of the wing. While proceeding downstream, a strong interaction between the vortices is observed for high angles of attack. The behavior of the vortex system and the influence on the high-lift performance of the configuration is characterized. In particular, the effect of the applied turbulence models of different types on the prediction of the vortex behavior is shown within this contribution.

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Section: Introductionmentioning

confidence: 63%

Numerical simulations of streamwise vortices on a high-lift wing

Landa

Radespiel

Wild³

2016

CEAS Aeronaut J

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“…The SA model is robust and sufficiently validated for the simulation of the flow around complex high-lift configurations. [9][10][11] The time-stepping was done by an implicit lower-upper symmetric Gauß-Seidel (LU-SGS) scheme. A central second-order scheme with Matrix dissipation was employed.…”

Section: Rans Methods -Model Mesh Solvermentioning

confidence: 99%

Investigation of the engine-gear vortex with LIDAR and CFD

Stephan¹,

Wildmann²,

Smalikho

et al. 2018

24th International Symposium on Atmospheric and Ocean Optics: Atmospheric Physics

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The final approach and touchdown of a landing aircraft is studied numerically with a hybrid RANS/LES approach, as well as a pulsed coherent LIDAR system. Particular emphasis is put on the ground effect, the engine-gear vortex and the wake vortex evolution before and after touchdown. We compare CFD results with LIDAR measurement data collected in a recent campaign at Vienna airport. The radial velocity method was applied to retrieve vortex position and circulation. The vortex structures predicted by the simulations are clearly visible in those measurements. Simulated tangential velocity profiles are compared with vortex model profiles. It is observed that the standard vortex model can be improved including mirror vortices.

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“…In order to enable a most accurate numerical predic-tion of maximum lift, only minor simplifications, inevitable for successful mesh generation, were introduced. 5 The unstructured, hybrid CFD mesh was generated using the commercial grid generation software CENTAUR TM . 6 Particular attention was dedicated to those geometric features most relevant for the development of the inboard wing vortex system which essentially determines overall high-lift performance.…”

Section: A Cfd Meshmentioning

confidence: 99%

Aeroelastic Effects in Maximum Lift Prediction of a Transport Aircraft and Comparison to Flight Data

Keye

Rohlmann

2014

32nd AIAA Applied Aerodynamics Conference

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The virtual determination of maximum lift performance of a transport aircraft configuration taking into account static aeroelastic deformations at steady-state flight conditions is described. Within the scope of the national research project HINVA (High-Lift IN-Flight VAlidation) a fluid-structure interaction approach based on high-fidelity numerical fluid dynamics and structural analysis methods has been applied to DLR's Airbus A320-232 ATRA research aircraft in high-lift configuration. Numerical aeroelastic analyses were performed using an in-house simulation procedure built around DLR's flow solver TAU and the commercial finite-element analysis code NASTRAN R . Numerical results were validated against experimental data obtained from the first HINVA flight test campaign in July 2012.

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Numerical Maximum Lift Predictions of a Realistic Commercial Aircraft in Landing Configuration

Cited by 17 publications

References 17 publications

Numerical simulations of streamwise vortices on a high-lift wing

Numerical simulations of streamwise vortices on a high-lift wing

Investigation of the engine-gear vortex with LIDAR and CFD

Aeroelastic Effects in Maximum Lift Prediction of a Transport Aircraft and Comparison to Flight Data

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