Advances in aircraft and spacecraft science

  • 제5권4호
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  • Pages.445-458
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  • 2018
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Supersonic flow bifurcation in twin intake models

  • 투고 : 2017.11.03
  • 심사 : 2018.03.21
  • 발행 : 2018.07.25
⟨ 이전 논문 다음 논문 ⟩

초록

Turbulent airflow in channels of rectangular cross section with symmetric centerbodies is studied numerically. Shock wave configurations formed in the channel and in front of the entrance are examined. Solutions of the unsteady Reynolds-averaged Navier-Stokes equations are obtained with finite-volume solvers of second-order accuracy. The solutions demonstrate an expulsion/swallowing of the shocks with variations of the free-stream Mach number or angle of attack. Effects of the centerbody length and thickness on the shock wave stability and flow bifurcation are examined. Bands of the Mach number and angle of attack, in which there exist non-unique flow fields, are identified.

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피인용 문헌

  1. Enlarge duct length optimization for suddenly expanded flows vol.7, pp.3, 2020, https://doi.org/10.12989/aas.2020.7.3.203