Near field sonic boom calculation of benchmark cases

Jiaye Gan, GeCheng Zha

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)

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 languageEnglish (US)
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
DOIs
StatePublished - 2015
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: Jan 5 2015Jan 9 2015

Other

Other53rd AIAA Aerospace Sciences Meeting, 2015
CountryUnited States
CityKissimmee
Period1/5/151/9/15

Fingerprint

Shock waves
Computational fluid dynamics
Experiments

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Gan, J., & Zha, G. (2015). Near field sonic boom calculation of benchmark cases. In 53rd AIAA Aerospace Sciences Meeting American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2015-1252

Near field sonic boom calculation of benchmark cases. / Gan, Jiaye; Zha, GeCheng.

53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Gan, J & Zha, G 2015, Near field sonic boom calculation of benchmark cases. in 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 53rd AIAA Aerospace Sciences Meeting, 2015, Kissimmee, United States, 1/5/15. https://doi.org/10.2514/6.2015-1252
Gan J, Zha G. Near field sonic boom calculation of benchmark cases. In 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA. 2015 https://doi.org/10.2514/6.2015-1252
Gan, Jiaye ; Zha, GeCheng. / Near field sonic boom calculation of benchmark cases. 53rd AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2015.
@inproceedings{f2d81b1eb7ba439f99c0f99fd1c1c112,
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",
year = "2015",
doi = "10.2514/6.2015-1252",
language = "English (US)",
isbn = "9781624103438",
booktitle = "53rd AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

}

TY - GEN

T1 - Near field sonic boom calculation of benchmark cases

AU - Gan, Jiaye

AU - Zha, GeCheng

PY - 2015

Y1 - 2015

N2 - 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.

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.

UR - http://www.scopus.com/inward/record.url?scp=84983003980&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84983003980&partnerID=8YFLogxK

U2 - 10.2514/6.2015-1252

DO - 10.2514/6.2015-1252

M3 - Conference contribution

AN - SCOPUS:84983003980

SN - 9781624103438

BT - 53rd AIAA Aerospace Sciences Meeting

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

ER -