Advances in aircraft and spacecraft science

  • 제1권4호
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  • Pages.399-408
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  • 2014
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Numerical simulations of convergent-divergent nozzle and straight cylindrical supersonic diffuser

  • Mehta, R.C. (Department of Aeronautical Engineering, Noorul Islam University) ;
  • Natarajan, G. (Department of Mechanical Civil Engineering, Noorul Islam University)
  • 투고 : 2014.04.15
  • 심사 : 2014.05.12
  • 발행 : 2014.10.25
⟨ 이전 논문 다음 논문 ⟩

초록

The flowfields inside a contour and a conical nozzle exhausting into a straight cylindrical supersonic diffuser are computed by solving numerically axisymmetric turbulent compressible Navier-Stokes equations for stagnation to ambient pressure ratios in the range 20 to 34. The diffuser inlet-to-nozzle throat area ratio and exit-to-throat area ratio are 21.77, and length-to-diameter ratio of the diffuser is 5. The flow characteristics of the conical and contour nozzle are compared with the help of velocity vector and Mach contour plots. The variations of Mach number along the centre line and wall of the conical nozzle, contour nozzle and the straight supersonic diffuser indicate the location of the shock and flow characteristics. The main aim of the present analysis is to delineate the flowfields of conical and contour nozzles operating under identical conditions and exhausting into a straight cylindrical supersonic diffuser.

키워드

참고문헌

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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