Supersonic flow past a gas jet obstacle emerging from a plate

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

doi:10.1007/bf01027359

Cited by 44 publications

(7 citation statements)

References 6 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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“…There are similarities between the injection jet and a solid obstacle. In [3,4,5] it was used analytical methods for considered the issue. In fact, the pattern formed in the case of the injection jet is similar to the flow pattern in the case of installation of the flow path blunt axially symmetric rigid body.…”

Section: Resultsmentioning

confidence: 99%

Study of Changes in the Aerodynamic Characteristics of the Axisymmetric Supersonic Vehicle in Case of Gas Blowing from the Lateral Surface

Kislovsky¹,

Звегинцев²

2017

dtetr

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Abstract.We consider the flow around the axisymmetric supersonic vehicle with the use of gas jetblowingfrom the lateral surface. The blowing is made in series of points at different distances from the nose fairing. The aim of the work was to determine the changes in aerodynamic forces and the formation of the moment, when jet of gasblowingin different parts of the supersonic vehicle. The study was conducted by numerical modeling of different cases of injection. As a result, data were obtained which showed the degree of influence not only jet thrust from the jet flow, but same the impact of the redistribution of the flow by body surface on the formation of aerodynamic forces and moments.

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“…The dimensions of the zones of p e r t u r b e d flow in the nozzles during the experiments were determined by three methods; from the distribution of the static pressure in the transverse sections of the nozzle; from the tracks of the flow in the visual representation compound on the wall of the nozzle in the perturbed flow zone [4];…”

Section: The Methods Of the Experimentsmentioning

confidence: 99%

The effect of the arrangement of the openings on the amplification factor during asymmetric gas blowing into a laval nozzle

Зеленцов¹,

Kremnev²,

Nesterov³

et al. 1984

Fluid Dyn

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In asymmetric blowing of a gas into the supersonic part of a nozzle the main flow is perturbed by the jet which is being blown. Two interaction regimes are distinguished.In the first the perturbation of the main flow does not extend to the side of the nozzle opposite to the blast: the central angle subtended by the perturbation of the exit section of the nozzle is 2y a < 180 ~ (Fig. i). This regime is characterized by the fact that the curvature of the nozzle has no effect on the magnitude of the lateral force.In the second regime the zone of the perturbed flow extends to the side of the nozzle opposite to the blast (2Ya > 180~and this leads to a decrease in the gradient of the lateral force with respect to the fldw rate of the gas which is being blown. The first regime has been studied in the most detail.The experimental data of [i] indicate the slight influence of the shape and the number of openings in the injection unit through which the blowing is taking place, and also of the distance between them, on the magnitude of the amplification factor X, which is tha ratio of the total lateral force F to the thrust F v of the secondary jet in the vacuum in the case of axisymmetric blowing of gas into a Laval nozzle.In [2] a study was made of the effect on the amplification factor of the location of the injector along the length of the supersonic part of the nozzle when a secondary gas is being blown through single cylindrical openings of different diameter d.Experimental data on the amplification factor were generalized into a single curve ([2], Fig. I) in dimensionless coordinates K ~ = K/Ka, Ll/d (K is the current value of the amplification factor, K a is the value of the amplification factor when gas is blown through axL opening located in the immediate vicinit[ of the eXito section).These data were obtained with combinations of the parameters G 2, a, and L 1 which guarantee that the condition 2"y a < 180 ~ O is fulfilled.IIere G 2 = G2/G 1 is the relative mass flow rate of the gas which is being blown, G 1 is the flow rate through the main nozzle, a is the angle between the axis of the blowing O channel and the axis of the main nozzle, L 1 ~ LI/L is the relative distance between the blowing section and the exit section of the nozzle, and L is the length of the supersonic part of the nozzle.The flow in a nozzle with gas being blown and with a perturbation extending to the side of the nozzle opposite to the blowing (2y a > 180 ~ ) has a number of peculiarities which determine the specific effecton the amplification factor of the way in which the blowing openings are distributed along the length of the nozzle and in the injection unit.In the present study, which is a continuation of [2], the amplification factor was experimentally determined in the case of a transverse gas jet being blown into the supersonic parts of axisymmetric nozzles with various dispositions of the openings alon~ the length of the nozzle and in the injection unit during processes characterized by the extension of the perturbation to the side ...

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Supersonic flow past a gas jet obstacle emerging from a plate

Cited by 44 publications

References 6 publications

Detailed flow physics of the supersonic jet interaction flow field

Detailed flow physics of the supersonic jet interaction flow field

Study of Changes in the Aerodynamic Characteristics of the Axisymmetric Supersonic Vehicle in Case of Gas Blowing from the Lateral Surface

The effect of the arrangement of the openings on the amplification factor during asymmetric gas blowing into a laval nozzle

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