Numerical study on flow separation of a transonic cascade

Zongjun Hu; GeCheng Zha; Jan Lepicovsky

Numerical study on flow separation of a transonic cascade

Zongjun Hu, GeCheng Zha, Jan Lepicovsky

Mechanical & Aerospace Engineering

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

1 Scopus citations

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

ASJC Scopus subject areas

Engineering(all)

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title = "Numerical study on flow separation of a transonic cascade",

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.",

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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.

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Y2 - 5 January 2004 through 8 January 2004

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