Near field sonic boom calculation of benchmark cases

Jiaye Gan; Gecheng Zha

doi:10.2514/6.2015-1252

Near field sonic boom calculation of benchmark cases

Jiaye Gan, Gecheng Zha

Mechanical & Aerospace Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

4 Scopus citations

Abstract

This paper validates the accuracy of a high order accuracy CFD code on predicting near field signatures of sonic boom propagation. The flow near the body is solved using a structured grid Euler solver with low diffusion E-CUSP schemes, 3rd order MUSCL scheme, and 3rd and 5th order WENO schemes. Three benchmark cases, including two non-lifting models and one lifting model, are calculated. The predicted results are in good agreement with that of experiment data. For the Delta wing configuration, the mesh provided by the workshop generates a smooth expansion wave at the off-track plane. When the mesh is refined, a shock coalesced by the compression waves from the wing tip is captured and it generates a weak shock wave interacting with the expansion.

Original language	English (US)
Title of host publication	53rd AIAA Aerospace Sciences Meeting
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624103438
DOIs	https://doi.org/10.2514/6.2015-1252
State	Published - 2015
Event	53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States Duration: Jan 5 2015 → Jan 9 2015

Publication series

Name	53rd AIAA Aerospace Sciences Meeting

Other

Other	53rd AIAA Aerospace Sciences Meeting, 2015
Country	United States
City	Kissimmee
Period	1/5/15 → 1/9/15

ASJC Scopus subject areas

Aerospace Engineering

Access to Document

10.2514/6.2015-1252

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title = "Near field sonic boom calculation of benchmark cases",

abstract = "This paper validates the accuracy of a high order accuracy CFD code on predicting near field signatures of sonic boom propagation. The flow near the body is solved using a structured grid Euler solver with low diffusion E-CUSP schemes, 3rd order MUSCL scheme, and 3rd and 5th order WENO schemes. Three benchmark cases, including two non-lifting models and one lifting model, are calculated. The predicted results are in good agreement with that of experiment data. For the Delta wing configuration, the mesh provided by the workshop generates a smooth expansion wave at the off-track plane. When the mesh is refined, a shock coalesced by the compression waves from the wing tip is captured and it generates a weak shock wave interacting with the expansion.",

author = "Jiaye Gan and Gecheng Zha",

note = "Publisher Copyright: {\textcopyright} 2015 by the American Institute of Aeronautics and Astronautics, Inc. Copyright: Copyright 2017 Elsevier B.V., All rights reserved.; 53rd AIAA Aerospace Sciences Meeting, 2015 ; Conference date: 05-01-2015 Through 09-01-2015",

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AB - This paper validates the accuracy of a high order accuracy CFD code on predicting near field signatures of sonic boom propagation. The flow near the body is solved using a structured grid Euler solver with low diffusion E-CUSP schemes, 3rd order MUSCL scheme, and 3rd and 5th order WENO schemes. Three benchmark cases, including two non-lifting models and one lifting model, are calculated. The predicted results are in good agreement with that of experiment data. For the Delta wing configuration, the mesh provided by the workshop generates a smooth expansion wave at the off-track plane. When the mesh is refined, a shock coalesced by the compression waves from the wing tip is captured and it generates a weak shock wave interacting with the expansion.

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