Unsteady flow computations of a slat with a blunt trailing edge

Mehdi R. Khorrami, Mert E. Berkman, Meelan Choudhari, Bart A. Singer, David P. Lockard, Kenneth Steven Brentner

Research output: Chapter in Book/Report/Conference proceedingConference contribution

14 Scopus citations

Abstract

A detailed computational study of a high-lift configuration was conducted. The unsteady Reynolds Averaged Navier-Stokes (RANS) computations focused on the accurate simulation of the local flow field of a slat having a blunt trailing edge. At a slat deflection angle of 30 degrees relative to the main element, the simulations reveal the presence of strong vortex shedding at the slat trailing edge. The resulting flow unsteadiness produces large amplitude propagating waves. The local spatial resolution of the computed solution is sufficiently fine to capture the nearfield structure and propagation direction of the generated sound. The calculated shedding frequency is in good agreement with the measured acoustic frequencies obtained at NASA Langley's Low Turbulence Pressure Tunnel. At a lower slat deflection angle of 20 degrees, the computation suggests that the shedding process is severely damped and that no waves propagate, in agreement with the acoustic measurements.

Original languageEnglish (US)
Title of host publication5th AIAA/CEAS Aeroacoustics Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9780000000002
StatePublished - Jan 1 1999
EventAeroacoustics Conference and Exhibit, AIAA/CEAS 1999 - Bellevue, United States
Duration: May 10 1999May 12 1999

Publication series

Name5th AIAA/CEAS Aeroacoustics Conference and Exhibit

Other

OtherAeroacoustics Conference and Exhibit, AIAA/CEAS 1999
CountryUnited States
CityBellevue
Period5/10/995/12/99

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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