Interaction between a supersonic flow and gas issuing from a hole in a plate

Glagolev, A. I.; Зубков, А. И.; Panov, Yu. A.

doi:10.1007/bf01013556

Cited by 24 publications

(6 citation statements)

References 9 publications

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“…A number of investigations aimed at the development of thrust vector control systems were carried out in the 1960s to study the pressure distribution in the region around the injector and the resulting normal force and pitching moment. 4,11,12 Several researchers 10,11,[13][14][15][16][17][18] analyzed this flow field through analytical models and experiments. However, these efforts have been only partially successful due in large part to the difficulty of experimentally measuring the local flow without disrupting it and in part, due to the inherent complexity of the flow physics involved.…”

Section: Introductionmentioning

confidence: 99%

Detailed flow physics of the supersonic jet interaction flow field

2009

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The supersonic jet interaction flow field generated by a sonic circular jet with a pressure ratio of 532 exhausting into a turbulent MACH 4.0 cross flow over a flat plate was investigated using numerical simulations. The simulations made use of the three-dimensional Reynolds-averaged Navier-Stokes ͑RANS͒ equations coupled with Wilcox's 1998 k-turbulence model. The numerical solution was validated with experimental data that include the pressure distribution on the flat plate, with an empirical formula for the height of the barrel shock, and with the Schlieren pictures showing the location and shape of the main shock formations. The simulations correctly captured the location and shape of the main flow features and compared favorably with the experimental pressure distribution on the flat plate. The validated numerical simulation was used to investigate in detail the flow physics. The flow field was found to be dominated by the shock formations and their coupling with the strong vortical structures. Three primary shock formations were observed: a barrel shock, a bow shock, and a separation-induced shock wave. While the general structure of the barrel shock was found to be similar to that of the underexpanded jet exhausting into a quiescent medium, two unique features distinguished the flow field: the concave indentation in the leeside of the recompression ͑barrel͒ shock and the folding of the windward side of the barrel shock due to an inner reflection line. The presence of the steep pressure gradients associated with the shocks creates strong vortical motions in the fluid. Six primary vortices were identified: ͑i͒ the well-known horseshoe vortex, ͑ii͒ an upper trailing vortex, ͑iii͒ two trailing vortices formed in the separation region and, aft of the bow shock wave, ͑iv͒ two more trailing vortices that eventually merge together into one single rotational motion. The low-pressure region aft of the injector was found to be generated by the combined effect of the concave indentation in the leeside of the barrel shock and the lower trailing vortices. The trailing vortices were found to be the main mechanism responsible for the mixing of the injectant with the freestream fluid.

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Section: Introductionmentioning

confidence: 99%

Detailed flow physics of the supersonic jet interaction flow field

2009

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“…The supersonic flow along a thin plate with a shock generator on the upper boundary is considered with the parameters corresponding to the experiments [12], where the freestream Mach number M 5, ∞ = the Reynolds number 6 Re 40 10 , = ⋅ the wall temperature w 300 K. T =…”

Section: Test Problemmentioning

confidence: 99%

“…The freestream parameters are as follows: M ∞ = 3.75, T ∞ = 629.43 K, 6 Re 10 , = Pr 0.7; = the jet temperature 0 800 K, T = the pressure ratio n is equal to 15. The data of numerical experiments on the interaction of shocks with the boundary layers for the slots of the different width are shown in Fig.…”

Section: Investigation Of the Jet Width Effectmentioning

confidence: 99%

Numerical simulations of shock-wave interaction with a boundary layer in the plane supersonic flows with jet injection

Beketaeva

Moisseyeva

Naimanova

2016

Thermophys. Aeromech.

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A supersonic air flow in a plane channel with a transverse turbulent jet of hydrogen injected through a slot on the bottom wall is simulated. The algorithm for solving the Favre-averaged Navier−Stokes equations for the flow of a perfect multispecies gas on the basis of the WENO scheme is proposed. The main attention is paid to the interaction of the shock-wave structure with the boundary layers on the upper and lower duct walls under the conditions of an internal turbulent flow. Namely, a detailed study of the structure of the flow is done, and separation and mixing depending on the jet slot width are investigated. It is found that in addition to well-known shock-wave structures produced by the interaction of the free stream with the transverse jet and the bow shock interaction with the boundary layers near the walls, an additional system of shock waves and the flow separation arise on the bottom wall downstream at some distance from the jet. The comparison with the experimental data is performed.

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“…Early studies of JISC mostly focused on the mixing mechanism. Experimental studies [1,2] observed the analogy in vortex structures and pressure distribution between the transverse jet and the cylinder disturbance in a supersonic flow, and thus proposed that jet penetration can be treated as an equivalent obstacle. Chenault et al [3] investigated the effect of different turbulence models on the modeling of jet disturbance, and found that Reynold's Stress Model (RSM) accurately predicted time-averaged characteristics and main flow structures of JISC, as well as captured the second flow.…”

Section: Introductionmentioning

confidence: 99%