CFD Analysis of Unsteady Separated Transonic Oscillation Cascade Aerodynamics

Xuedong Zhou, J. Mitch Wolff, Mitch Wolff

Research output: Contribution to journalArticlepeer-review

Abstract

With an improved algebraic mesh-deforming algorithm, STAR-CD, a commercial computational fluid dynamics (CFD) solver is employed for the numerical analysis of a transonic oscillating linear cascade of advanced design blades. The center blade oscillates 0.6-degrees about the middle cord. The numerical simulation is conducted for a frequency range from 200 Hz to 500 Hz. A hybrid grid, which utilizes a structured O-grid around the airfoil and an unstructured grid everywhere else is employed. The Spalart-Allmaras (S-A), one equation turbulence model, along with other two equation k - ε models, are also utilized for the steady state simulation. The S-A turbulence model provided significantly better steady state results in the separated flow region than the k - ε model. The agreement between the experimental data and CFD prediction was better for the M=0.8 unsteady results than the M=0.5 on the suction surface. This could be attributed to a larger unsteady variation in the reattachment location for the M=0.5 results than the M=0.8. Finally, the time average of the unsteady skin friction coefficient is significantly different than the steady state value indicating nonlinear unsteady aerodynamics are significant for this analysis.

Original languageAmerican English
JournalInternational Journal of Turbo and Jet-Engines
Volume21
StatePublished - Jan 1 2004

Keywords

  • CFD analysis
  • cascade aerodynamics
  • oscillation
  • separated
  • transonic
  • unsteady

Disciplines

  • Engineering
  • Materials Science and Engineering
  • Mechanical Engineering

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