Separation control on an airfoil using repetitive laser pulses

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

Abstract

Two-dimensional Navier-Stokes equation was numerically solved to reproduce dynamics of a flow separation under supersonic flow with Mach number of 1.7. The repetitive pulses were irradiated to the under surface of the diamond wing to control the flow separation induced on the upper surface. A strong blast wave was generated from a focal point of the repetitive pulses because of a rapid gas heating. The expansion wave was induced from the trailing edge when the blast wave with the supersonic speed propagated from the under to upper surfaces. The separation region on the upper surface became smaller by irradiating the repetitive pulses on the under surface because the expansion wave induced from the trailing edge interacted with a recompres-sion wave and relaxed an inverse pressure gradient on the upper surface. A lift-to-drag ratio of the wing was improved by utilizing an energy deposition of the repetitive pulses because of a decrease in the pressure on the upper surface and an increase in the pressure on the under surface. An effectiveness of a “contactless” flow control device using the repetitive pulses was revealed by our numerical simulation.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
Publication statusPublished - 2018
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 2018 Jan 82018 Jan 12

Publication series

NameAIAA Aerospace Sciences Meeting, 2018
Number210059

Other

OtherAIAA Aerospace Sciences Meeting, 2018
Country/TerritoryUnited States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • Aerospace Engineering

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