A numerical test of viscous transonic flow with the TVD scheme: AIAA Paper# 99-4838

Xinjun Cui; A.I. Ruban; Yiyun Wang

doi:10.2514/6.1999-4838

A numerical test of viscous transonic flow with the TVD scheme: AIAA Paper# 99-4838

Xinjun Cui, A.I. Ruban, Yiyun Wang

SCEDT Engineering

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

Abstract

The two-dimensional compressible unsteady Navier-Stokes equations are computed with a second-order accurate Non-MUSCL TVD scheme to obtain the steady-state solution according to the time-dependent method. The shock wave is successfully captured with a good resolution at both transonic and supersonic regions, and the capturing process is analysed. The comparison of the higher-order accurate is made in order to demonstrate the difference of the resolution to shock waves. The process of approaching the steady state with the time-dependent method is explained. In addition, the interation of shock waves for different Mach numbers and ifferent angles of attack are described by showing the local flow situation at the interaction region.

Original language	English
Title of host publication	American Institute of Aeronautics and Astronautics
Publisher	American Institute of Aeronautics and Astronautics Inc. (AIAA)
DOIs	https://doi.org/10.2514/6.1999-4838
Publication status	Published - 22 Aug 2012
Event	9th International Space Planes and Hypersonic Systems and Technologies Conference - Norfolk, United States Duration: 1 Nov 1999 → 5 Nov 1999 https://arc.aiaa.org/doi/book/10.2514/MHYTASP99

Conference

Conference	9th International Space Planes and Hypersonic Systems and Technologies Conference
Country/Territory	United States
City	Norfolk
Period	1/11/99 → 5/11/99
Internet address	https://arc.aiaa.org/doi/book/10.2514/MHYTASP99

Access to Document

10.2514/6.1999-4838Licence: CC BY

Cite this

@inproceedings{5a3d308fba734f2b90b44b21518b4e21,

title = "A numerical test of viscous transonic flow with the TVD scheme: AIAA Paper# 99-4838",

abstract = "The two-dimensional compressible unsteady Navier-Stokes equations are computed with a second-order accurate Non-MUSCL TVD scheme to obtain the steady-state solution according to the time-dependent method. The shock wave is successfully captured with a good resolution at both transonic and supersonic regions, and the capturing process is analysed. The comparison of the higher-order accurate is made in order to demonstrate the difference of the resolution to shock waves. The process of approaching the steady state with the time-dependent method is explained. In addition, the interation of shock waves for different Mach numbers and ifferent angles of attack are described by showing the local flow situation at the interaction region.",

author = "Xinjun Cui and A.I. Ruban and Yiyun Wang",

year = "2012",

month = aug,

day = "22",

doi = "10.2514/6.1999-4838",

language = "English",

booktitle = "American Institute of Aeronautics and Astronautics",

publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

address = "United States",

note = "9th International Space Planes and Hypersonic Systems and Technologies Conference ; Conference date: 01-11-1999 Through 05-11-1999",

url = "https://arc.aiaa.org/doi/book/10.2514/MHYTASP99",

}

Cui, X, Ruban, AI & Wang, Y 2012, A numerical test of viscous transonic flow with the TVD scheme: AIAA Paper# 99-4838. in American Institute of Aeronautics and Astronautics. American Institute of Aeronautics and Astronautics Inc. (AIAA), 9th International Space Planes and Hypersonic Systems and Technologies Conference, Norfolk, United States, 1/11/99. https://doi.org/10.2514/6.1999-4838

TY - GEN

T1 - A numerical test of viscous transonic flow with the TVD scheme

T2 - 9th International Space Planes and Hypersonic Systems and Technologies Conference

AU - Cui, Xinjun

AU - Ruban, A.I.

AU - Wang, Yiyun

PY - 2012/8/22

Y1 - 2012/8/22

N2 - The two-dimensional compressible unsteady Navier-Stokes equations are computed with a second-order accurate Non-MUSCL TVD scheme to obtain the steady-state solution according to the time-dependent method. The shock wave is successfully captured with a good resolution at both transonic and supersonic regions, and the capturing process is analysed. The comparison of the higher-order accurate is made in order to demonstrate the difference of the resolution to shock waves. The process of approaching the steady state with the time-dependent method is explained. In addition, the interation of shock waves for different Mach numbers and ifferent angles of attack are described by showing the local flow situation at the interaction region.

AB - The two-dimensional compressible unsteady Navier-Stokes equations are computed with a second-order accurate Non-MUSCL TVD scheme to obtain the steady-state solution according to the time-dependent method. The shock wave is successfully captured with a good resolution at both transonic and supersonic regions, and the capturing process is analysed. The comparison of the higher-order accurate is made in order to demonstrate the difference of the resolution to shock waves. The process of approaching the steady state with the time-dependent method is explained. In addition, the interation of shock waves for different Mach numbers and ifferent angles of attack are described by showing the local flow situation at the interaction region.

U2 - 10.2514/6.1999-4838

DO - 10.2514/6.1999-4838

M3 - Conference contribution

BT - American Institute of Aeronautics and Astronautics

PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)

Y2 - 1 November 1999 through 5 November 1999

ER -

A numerical test of viscous transonic flow with the TVD scheme: AIAA Paper# 99-4838

Abstract

Conference

Access to Document

Fingerprint

Cite this