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WM_AIAA_Journal_Accepted_23-09-2020.pdf (12.12 MB)

Large-eddy simulation with modeled wall stress for complex aerodynamics and stall prediction

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journal contribution
posted on 2021-02-16, 09:45 authored by M Angelino, P Fernández-Yáñez, Hao XiaHao Xia, Gary PageGary Page
The aerodynamics of aircraft high-lift devices at near-stall conditions is particularly difficult to predict numerically. The computational requirements for accurate wall-resolved large-eddy simulations are currently prohibitive, whereas Reynolds-averaged Navier–Stokes (RANS) models are generally reliable only for low angles of attack with fully attached boundary layers. Methods such as detached-eddy simulation resolve unsteadiness of the outer boundary layer and can predict separation, but they rely upon a thick RANS layer and highly stretched cells that damp the resolved turbulent fluctuations near the wall. An alternative approach, adopted here, is to extend the LES down to the wall, employing a relatively large near-wall normal grid spacing and avoiding grid stretching and high aspect ratios near the wall. A boundary condition then applies the correct wall shear stress as provided by a semiempirical wall model. An adaptive formulation of this wall-modeled large-eddy simulation is presented here and validated using realistic test cases. Validation using a channel flow case at a range of Reynolds numbers demonstrates accurate results with a seamless transition between fully resolved (y+≈2) and wall resolved (y+≈50). Predictions of the MD-30P/30N airfoil using a modest grid with y+≈100 give excellent agreement with experiments and correctly predict CLmax. Finally, the method is demonstrated for the NASA High-Lift Common Research Model providing surface pressure coefficients and velocity profiles. The predictions using a 50-million-cell mesh (for a full aircraft half-model) are in good agreement with considerably finer-grid RANS solutions. The presented method has considerable potential because it can produce accurate solutions to challenging engineering problems involving separation with modest grid and computational requirements while being robust to variations in near-wall grid spacing.

Funding

Proposal for a Tier 2 Centre - HPC Midlands Plus

Engineering and Physical Sciences Research Council

Find out more...

Innovate U.K. “ACAPELLA” project (reference number 113086) in collaboration with Rolls–Royce plc.

University of Castilla–La Mancha [2015/4062]

History

School

  • Aeronautical, Automotive, Chemical and Materials Engineering

Department

  • Aeronautical and Automotive Engineering

Published in

AIAA Journal

Volume

59

Issue

4

Pages

1225-1237

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Version

  • AM (Accepted Manuscript)

Rights holder

© The Authors

Publisher statement

This paper was accepted for publication in the journal AIAA Journal and the definitive published version is available at https://doi.org/10.2514/1.J059481.

Acceptance date

2020-09-23

Publication date

2020-12-29

Copyright date

2021

ISSN

0001-1452

eISSN

1533-385X

Language

  • en

Depositor

Prof Gary Page. Deposit date: 15 February 2021

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