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Dataset for direct numerical simulations of a transonic airfoil at a Reynolds number of Re=500,000

Dataset for direct numerical simulations of a transonic airfoil at a Reynolds number of Re=500,000
Dataset for direct numerical simulations of a transonic airfoil at a Reynolds number of Re=500,000
These three folders comprise datasets corresponding to figure 5, figure 6 and figure 8 in Zauner et al. (2018):M. Zauner, N. De Tullio and N. Sandham, "Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers." in the AIAA Journal, 2018. https://doi.org/10.2514/1.J057335All simulations were carried out at a Mach number of M=0.7 and a Reynolds number of Re=500,000.Description of content: - Fig5: Average skin-friction coefficient and pressure coefficient as a function of axial chord position. - Fig6: Skin friction as a function of time and space for the reference solution (case C0), the simulation with a grid refined in the xy-plane (G1) and the simulation with the reference xy-plane refined in the spanwise direction (G2). - Fig8: Instantaneous lift coefficient and surface density as function of time. The surface density is recorded at 10%, 30%, 50%, 70% of the axial chord length and at the leading- as well as trailing edge. - Movie showing vorticity contours in red and blue, and strong pressure gradients in the background.
Direct numerical simulation, Moderate Reynolds numbers, Transonic airfoil
University of Southampton
Zauner, Markus
c0207f79-62cc-4909-8aa0-6bb9d99e1ea3
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97
De Tullio, Nicola
db4397b2-3fab-476c-a0f4-4caf9848d5f7
Zauner, Markus
c0207f79-62cc-4909-8aa0-6bb9d99e1ea3
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97
De Tullio, Nicola
db4397b2-3fab-476c-a0f4-4caf9848d5f7

Zauner, Markus (2018) Dataset for direct numerical simulations of a transonic airfoil at a Reynolds number of Re=500,000. University of Southampton doi:10.5258/SOTON/D0468 [Dataset]

Record type: Dataset

Abstract

These three folders comprise datasets corresponding to figure 5, figure 6 and figure 8 in Zauner et al. (2018):M. Zauner, N. De Tullio and N. Sandham, "Direct numerical simulations of transonic flow around an airfoil at moderate Reynolds numbers." in the AIAA Journal, 2018. https://doi.org/10.2514/1.J057335All simulations were carried out at a Mach number of M=0.7 and a Reynolds number of Re=500,000.Description of content: - Fig5: Average skin-friction coefficient and pressure coefficient as a function of axial chord position. - Fig6: Skin friction as a function of time and space for the reference solution (case C0), the simulation with a grid refined in the xy-plane (G1) and the simulation with the reference xy-plane refined in the spanwise direction (G2). - Fig8: Instantaneous lift coefficient and surface density as function of time. The surface density is recorded at 10%, 30%, 50%, 70% of the axial chord length and at the leading- as well as trailing edge. - Movie showing vorticity contours in red and blue, and strong pressure gradients in the background.

Video
movie_vort.mp4 - Other
Available under License Creative Commons Attribution.
Download (147MB)
Archive
dataset_AIAA_Journal.tar - Dataset
Available under License Creative Commons Attribution.
Download (984MB)
Text
README_updated_11042019.txt - Text
Available under License Creative Commons Attribution.
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More information

Published date: 2018
Keywords: Direct numerical simulation, Moderate Reynolds numbers, Transonic airfoil
Organisations: Education Hub, Aerodynamics & Flight Mechanics Group, Aeronautics, Astronautics & Comp. Eng

Identifiers

Local EPrints ID: 427287
URI: http://eprints.soton.ac.uk/id/eprint/427287
PURE UUID: 6e39db16-deec-4430-b4ae-619ce4bea161
ORCID for Markus Zauner: ORCID iD orcid.org/0000-0002-6644-2990
ORCID for Neil Sandham: ORCID iD orcid.org/0000-0002-5107-0944

Catalogue record

Date deposited: 10 Jan 2019 17:31
Last modified: 12 Apr 2019 00:36

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