Numerical study on flow separation of a transonic cascade

Zongjun Hu, GeCheng Zha, Jan Lepicovsky

Research output: Chapter in Book/Report/Conference proceedingConference 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 languageEnglish
Title of host publicationAIAA Paper
Pages2119-2125
Number of pages7
StatePublished - Jul 1 2004
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 5 2004Jan 8 2004

Other

Other42nd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/5/041/8/04

ASJC Scopus subject areas

  • Engineering(all)

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  • Cite this

    Hu, Z., Zha, G., & Lepicovsky, J. (2004). Numerical study on flow separation of a transonic cascade. In AIAA Paper (pp. 2119-2125)