On choice of turbulence models and grid parameters for computation of flows in diffuser ducts

Mingazov, B. G.; Davletshin, I. S.

doi:10.3103/s1068799811040064

Cited by 2 publications

(2 citation statements)

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“…There is a unique combination of curves known as characteristic curves equations will be solved along the flow lines which have formed into flow net, these equations are solved waves propagating on the Mach lines in the direction waves in viscous flow results in a huge pressure gradient waves and boundary layer [4]. So the Prandtl order to straighten the flow.…”

Section: Design Methodology Nozzlementioning

confidence: 99%

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Design and Analysis of Two Throat Wind Tunnel

Shivaprasad¹,

Pai²,

Pai

et al. 2017

IJMPERD

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To aid in understanding the concepts of aerodynamics, wind tunnels are used. The aim of this paper is to design and analyze a two throat supersonic wind tunnel to give a better start-up condition at supersonic speeds. As the tunnel design involves high complexity, it is generally convenient to divide into segments. Initially, nozzle segment is developed using the method of characteristics (MOC) because, a careful designed nozzle is vital for tunnel function. In the next step, a settling chamber is introduced at the nozzle exit to straighten the flow, just before it enters the test section and the diffuser is designed to reduce the losses related to shocks attached. As we know that second throat at the diffuser section plays an important role in starting of a supersonic tunnel, so the area of the second throat is increased. In next phase, all segments are integrated and analyzed using the commercial code. Numerical analysis carried out reveals that the acceptable numerical accuracy is achieved with practice levels of grid resolution (300 x 30,) with the assumption that in absence of separation, low turbulence intensifies due to the effect of large acceleration along the downstream of the tunnel. The flow solutions give a better insight of understanding the flows, to investigate the effect of numerical code and grid independence. From this work, the necessity of grid dependence study and to the quantification of numerical error has been addressed by representing the computational results in complicated airways.

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Section: Design Methodology Nozzlementioning

confidence: 99%

“…As the presence of a huge pressure gradient, boundary layer separation due to the interaction between sh waves and boundary layer [4]. So the Prandtl-Meyer flow will seek to avoid the formation of oblique shock wave in the a finite number of grid points is susceptible with a truncation error order terms are neglected.…”

Section: Test Sectionmentioning

confidence: 99%