Abstract
The 3D compressible Navier-Stokes equations with Baldwin-Lomax turbulence model are solved to study the flow separation phenomenon in a NASA Transonic Flutter Cascade. The influence of the incidence angle and the inlet Mach number on the flow pattern in the cascade is numerically studied. When the incoming flow is subsonic, increasing the incidence angle generates a large separation region starting from the leading edge on the suction surface. Higher subsonic inlet Mach number results in a larger separation region. The separation region shrinks and moves downstream when the inlet Mach number is increased to supersonic due to the shock wave boundary layer interaction.
| Original language | English |
|---|---|
| Title of host publication | AIAA Paper |
| Pages | 2126-2132 |
| Number of pages | 7 |
| State | Published - Jul 1 2004 |
| Event | 42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: Jan 5 2004 → Jan 8 2004 |
Other
| Other | 42nd AIAA Aerospace Sciences Meeting and Exhibit |
|---|---|
| Country | United States |
| City | Reno, NV |
| Period | 1/5/04 → 1/8/04 |
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ASJC Scopus subject areas
- Engineering(all)
Cite this
Numerical study on flow separation of a transonic cascade. / Hu, Zongjun; Zha, GeCheng; Lepicovsky, Jan.
AIAA Paper. 2004. p. 2126-2132.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Numerical study on flow separation of a transonic cascade
AU - Hu, Zongjun
AU - Zha, GeCheng
AU - Lepicovsky, Jan
PY - 2004/7/1
Y1 - 2004/7/1
N2 - The 3D compressible Navier-Stokes equations with Baldwin-Lomax turbulence model are solved to study the flow separation phenomenon in a NASA Transonic Flutter Cascade. The influence of the incidence angle and the inlet Mach number on the flow pattern in the cascade is numerically studied. When the incoming flow is subsonic, increasing the incidence angle generates a large separation region starting from the leading edge on the suction surface. Higher subsonic inlet Mach number results in a larger separation region. The separation region shrinks and moves downstream when the inlet Mach number is increased to supersonic due to the shock wave boundary layer interaction.
AB - The 3D compressible Navier-Stokes equations with Baldwin-Lomax turbulence model are solved to study the flow separation phenomenon in a NASA Transonic Flutter Cascade. The influence of the incidence angle and the inlet Mach number on the flow pattern in the cascade is numerically studied. When the incoming flow is subsonic, increasing the incidence angle generates a large separation region starting from the leading edge on the suction surface. Higher subsonic inlet Mach number results in a larger separation region. The separation region shrinks and moves downstream when the inlet Mach number is increased to supersonic due to the shock wave boundary layer interaction.
UR - http://www.scopus.com/inward/record.url?scp=2942711529&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=2942711529&partnerID=8YFLogxK
M3 - Conference contribution
SP - 2126
EP - 2132
BT - AIAA Paper
ER -