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 | |
| State | Published - 2015 |
| Event | 53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States Duration: Jan 5 2015 → Jan 9 2015 |
Other
| Other | 53rd AIAA Aerospace Sciences Meeting, 2015 |
|---|---|
| Country | United States |
| City | Kissimmee |
| Period | 1/5/15 → 1/9/15 |
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ASJC Scopus subject areas
- Aerospace Engineering
Cite this
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 proceeding › Conference contribution
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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 -