Numerical simulation of transonic shock-vortex interaction flow around the VFE-2 delta wing based on MDDES

Zhao Ke, Zheng Hong Gao, Jiang Tao Huang

Research output: Contribution to conferencePaperpeer-review

Abstract

The transonic flow around the 65° Delta wing configuration with sharp leading edge is presented. The occurrence of shock on delta wings introduces complex shock/vortex interactions, particularly at moderate-to-high angles of incidence. These interactions can make a significant difference to the vortex breakdown. Transonic vortical flow and vortex breakdown is one aspect of the second "International Vortex Flow Experiment" (VFE-2). This investigation considers complex flowfield the 65° Delta wing using modified delayed detached eddy simulation(MDDES) . The time-averaged pressure is compared with the experiment data to validate the method. The shocks in the flow field are investigated and the interaction of the vortex and the shock waves is also studied. The unsteady characteristic of the vortex breakdown is analyzed by studying the Power Spectral Density (PSD) of time history of density at the probe points.

Original languageEnglish
Pages1645-1656
Number of pages12
StatePublished - 2012
Event28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 - Brisbane, Australia
Duration: 23 Sep 201228 Sep 2012

Conference

Conference28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012
Country/TerritoryAustralia
CityBrisbane
Period23/09/1228/09/12

Keywords

  • Cross-flow shock
  • MDDES
  • Shock/vortex interactions
  • Vortex breakdown

Fingerprint

Dive into the research topics of 'Numerical simulation of transonic shock-vortex interaction flow around the VFE-2 delta wing based on MDDES'. Together they form a unique fingerprint.

Cite this