Aerothermal exploration of reaction control jet in supersonic crossflow at high altitude

Murty, M.S.R. Chandra; Bhandarkar, Anand; Chakraborty, Debasis

doi:10.1016/j.ast.2016.01.004

Cited by 10 publications

(1 citation statement)

References 17 publications

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“…Flow parameters and skin temperature distributions caused by aerodynamic heating were simulated and analyzed by Murty for a high speed (∼ 5Ma) aerospace vehicle at about 25 km using commercial CFD code. [19] However, according to the published papers, the study on cavity configuration for hypersonic speeds in near space has rarely been investigated, probably because of the difficulties in experimentally measuring reliable data at hypersonic condition and the rarefied gas effects in near space, which motivates the current work.…”

Section: Introductionmentioning

confidence: 99%

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method*

et al. 2021

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Near space has been paid more and more attentionin recent years due to its military application value. However, flow characteristics of some fundamental configurations (e.g., the cavity) in near space have rarely been investigated due to rarefied gas effects, which make the numerical simulation methods based on continuous flow hypothesis lose validity. In this work, the direct simulation Monte Carlo (DSMC), one of the most successful particle simulation methods in treating rarefied gas dynamics, is employed to explore flow characteristics of a hypersonic cavity with sweepback angle in near space by considering a variety of cases, such as the cavity at a wide range of altitudes 20–60 km, the cavity at freestream Mach numbers of 6–20, and the cavity with a sweepback angle of 30°–90°. By analyzing the simulation results, flow characteristics are obtained and meanwhile some interesting phenomena are also found. The primary recirculation region, which occupies the most area of the cavity, causes pressure and temperature stratification due to rotational motion of fluid inside it, whereas the pressure and temperature in the secondary recirculation region, which is a small vortex and locates at the lower left corner of the cavity, change slightly due to low-speed movement of fluid inside it. With the increase of altitude, both the primary and secondary recirculation regions contract greatly and it causes them to separate. A notable finding is that rotation direction of the secondary recirculation region would be reversed at a higher altitude. The overall effect of increasing the Mach number is that the velocity, pressure, and temperature within the cavity increase uniformly. The maximum pressure nearby the trailing edge of the cavity decreases rapidly as the sweepback angle increases, whereas the influence of sweepback angle on velocity distribution and maximum temperature within the cavity is slight.

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Section: Introductionmentioning

confidence: 99%

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method*

et al. 2021

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Numerical simulation on thermal and mass diffusion of MMH–NTO bipropellant thruster plume flow using global kinetic reaction model

Lee

2019

Aerospace Science and Technology

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Large eddy simulation of transverse single/double jet in supersonic crossflow

Zhao

Bian

et al. 2019

Aerospace Science and Technology

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In this paper, large eddy simulation of transverse sonic single/double hydrogen jets into supersonic Mach 2 crossflow have been carried out to investigate the complex flow structures and the mixing performance. Detailed turbulence characteristics, in terms of the instantaneous and mean flow fields, the vortex structures and their evolutions, the turbulence kinetic energy and the Reynolds shear stress distributions, the maximum hydrogen mass fraction and jet penetration, have been provided. Results of the two-dimensional and three-dimensional streamlines illustrate that the trailing counter-rotating vortex pairs (TCVP), the secondary TCVP of primary jet and the horseshoe vortex can merge and form a new horseshoe vortex. Three counter-rotating vortex pairs (CVP) are formed in the downstream of secondary jet: the CVP-B due to interactions between the supersonic crossflow and secondary jet; the CVP-C due to interactions between the supersonic crossflow, primary and secondary jets; and the CVP-D due to interactions of the supersonic crossflow and primary jet. The presence of primary jet flow alters the Reynolds shear stress distributions after the secondary injection with the influence of these large-scale structures. In addition, the two-stage jet injection system is proved to yield a better mixing performance than the single jet system.

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Aerothermal exploration of reaction control jet in supersonic crossflow at high altitude

Cited by 10 publications

References 17 publications

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method*

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method*

Numerical simulation on thermal and mass diffusion of MMH–NTO bipropellant thruster plume flow using global kinetic reaction model

Large eddy simulation of transverse single/double jet in supersonic crossflow

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