Near field sonic boom analysis with HUNS3D solver

Boping Ma, Gang Wang, Jiong Ren, Ye Zhengyin, GeCheng Zha

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

3 Citations (Scopus)

Abstract

Accurate analysis of sonic boom pressure signature using Computational Fluid Dynamics (CFD) is still a challenging task. In this paper, four benchmark cases including two axisymmetric body, a simple delta wing body and a full configuration includes fuselage, wing, tail, flow-through nacelles, and blade wing were computed with a Reynold-averaged Navier-Stokes (RANS) based flow solver to predicted the near field sonic boom signature. The computed results from CFD agree well with the measured data in wind tunnel experiment. The effects of geometry equivalent radius, grid size, turbulence model and spatial discretization schemes are investigated and discussed.

Original languageEnglish (US)
Title of host publication55th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624104473
DOIs
StatePublished - 2017
Event55th AIAA Aerospace Sciences Meeting - Grapevine, United States
Duration: Jan 9 2017Jan 13 2017

Other

Other55th AIAA Aerospace Sciences Meeting
CountryUnited States
CityGrapevine
Period1/9/171/13/17

Fingerprint

Computational fluid dynamics
Fuselages
Turbulence models
Wind tunnels
Geometry
Experiments

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Ma, B., Wang, G., Ren, J., Zhengyin, Y., & Zha, G. (2017). Near field sonic boom analysis with HUNS3D solver. In 55th AIAA Aerospace Sciences Meeting [AIAA 2017-0038] American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2017-0038

Near field sonic boom analysis with HUNS3D solver. / Ma, Boping; Wang, Gang; Ren, Jiong; Zhengyin, Ye; Zha, GeCheng.

55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017. AIAA 2017-0038.

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

Ma, B, Wang, G, Ren, J, Zhengyin, Y & Zha, G 2017, Near field sonic boom analysis with HUNS3D solver. in 55th AIAA Aerospace Sciences Meeting., AIAA 2017-0038, American Institute of Aeronautics and Astronautics Inc., 55th AIAA Aerospace Sciences Meeting, Grapevine, United States, 1/9/17. https://doi.org/10.2514/6.2017-0038
Ma B, Wang G, Ren J, Zhengyin Y, Zha G. Near field sonic boom analysis with HUNS3D solver. In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc. 2017. AIAA 2017-0038 https://doi.org/10.2514/6.2017-0038
Ma, Boping ; Wang, Gang ; Ren, Jiong ; Zhengyin, Ye ; Zha, GeCheng. / Near field sonic boom analysis with HUNS3D solver. 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017.
@inproceedings{32f320d1fb2440cd846e3f20b446a522,
title = "Near field sonic boom analysis with HUNS3D solver",
abstract = "Accurate analysis of sonic boom pressure signature using Computational Fluid Dynamics (CFD) is still a challenging task. In this paper, four benchmark cases including two axisymmetric body, a simple delta wing body and a full configuration includes fuselage, wing, tail, flow-through nacelles, and blade wing were computed with a Reynold-averaged Navier-Stokes (RANS) based flow solver to predicted the near field sonic boom signature. The computed results from CFD agree well with the measured data in wind tunnel experiment. The effects of geometry equivalent radius, grid size, turbulence model and spatial discretization schemes are investigated and discussed.",
author = "Boping Ma and Gang Wang and Jiong Ren and Ye Zhengyin and GeCheng Zha",
year = "2017",
doi = "10.2514/6.2017-0038",
language = "English (US)",
booktitle = "55th AIAA Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc.",

}

TY - GEN

T1 - Near field sonic boom analysis with HUNS3D solver

AU - Ma, Boping

AU - Wang, Gang

AU - Ren, Jiong

AU - Zhengyin, Ye

AU - Zha, GeCheng

PY - 2017

Y1 - 2017

N2 - Accurate analysis of sonic boom pressure signature using Computational Fluid Dynamics (CFD) is still a challenging task. In this paper, four benchmark cases including two axisymmetric body, a simple delta wing body and a full configuration includes fuselage, wing, tail, flow-through nacelles, and blade wing were computed with a Reynold-averaged Navier-Stokes (RANS) based flow solver to predicted the near field sonic boom signature. The computed results from CFD agree well with the measured data in wind tunnel experiment. The effects of geometry equivalent radius, grid size, turbulence model and spatial discretization schemes are investigated and discussed.

AB - Accurate analysis of sonic boom pressure signature using Computational Fluid Dynamics (CFD) is still a challenging task. In this paper, four benchmark cases including two axisymmetric body, a simple delta wing body and a full configuration includes fuselage, wing, tail, flow-through nacelles, and blade wing were computed with a Reynold-averaged Navier-Stokes (RANS) based flow solver to predicted the near field sonic boom signature. The computed results from CFD agree well with the measured data in wind tunnel experiment. The effects of geometry equivalent radius, grid size, turbulence model and spatial discretization schemes are investigated and discussed.

UR - http://www.scopus.com/inward/record.url?scp=85023626541&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85023626541&partnerID=8YFLogxK

U2 - 10.2514/6.2017-0038

DO - 10.2514/6.2017-0038

M3 - Conference contribution

BT - 55th AIAA Aerospace Sciences Meeting

PB - American Institute of Aeronautics and Astronautics Inc.

ER -