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A Computational Study on the Shock Structure and Thrust Performance of a Supersonic Nozzle with Overexpanded Flow

과대팽창이 발생하는 초음속노즐의 충격파 구조와 추력성능에 대한 수치적 연구

  • Bae, Dae Seok (Department of Mechanical Engineering, Pukyong National University) ;
  • Choi, Hyun Ah (Department of Mechanical Engineering, Graduate School, Pukyong National University) ;
  • Kam, Ho Dong (Defense R&D Center, Hanwha Corporation) ;
  • Kim, Jeong Soo (Department of Mechanical Engineering, Pukyong National University)
  • Received : 2014.06.08
  • Accepted : 2014.07.15
  • Published : 2014.08.01

Abstract

Overexpanded flow of an axisymmetric thruster nozzle is numerically simulated to investigate effects of nozzle pressure ratio (NPR) on the shock structure and thrust performance. The Reynolds-averaged Navier-Stokes equations with k-${\omega}$ SST turbulence model are solved utilizing FLUENT solver. As the NPR is raised, thrust performance monotonically increases with the shock structure and flow-separation point being pushed toward the nozzle exit. It is also discussed that the flow structure at nozzle-exit plane which is immediately affected by a position of nozzle-interior shocks and expansion waves, has strong influence upon the thrust performance of thruster nozzle.

Acknowledgement

Supported by : 부경대학교

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