Side Jet Aerodynamic Interaction on a Blunt Body in Hypersonic Flow.

Kurita, Minoru; Okada, Takumi; Nakamura, Yu

doi:10.2322/jjsass.50.394

Cited by 4 publications

(4 citation statements)

References 15 publications

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“…The behavior of sensors 1, 6, and 7 in Figures 22 and 23 suggested the same phenomenon. Referring to Kurita et al, 14 with the changes in the angle of attack, the upstream pressure was reduced, but the dimension of the region was increased. On the other hand, the changes in sensor 2 were slightly different from those in sensor 1.…”

Section: Supersonic Free Streammentioning

confidence: 92%

An experimental study of binary lateral jets on a standard model in subsonic, transonic, and supersonic cross-flows

Doolabi

Sabour

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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There are numerous aerodynamic and nonaerodynamic methods to control flying devices, one of which is lateral jets, i.e. a high-speed method with convenient operation at low speeds or high altitudes. In this research, a new arrangement of lateral jets is examined by testing in a wind tunnel. The test is conducted on the Basic Finner model. In this design, the jets at the top and bottom of the model are arranged in pairs and parallel to each other. This combination, in addition to controlling pitch channel, provides the necessary conditions to control the roll channel. In this paper, pressure distribution is examined in the upstream and downstream areas as well as middle of jets. The flow visualization method is also used. The results are provided for subsonic, transonic, and supersonic free flow regime at the positive and negative angles of attacks. In the subsonic and supersonic flows, the achievements of the binary jets are the further pressure reduction on the middle line of jets compared with the same position at downstream of a single jet, and maintaining a high-pressure area of a single jet at the upstream of jets compared with the upstream area. However, the pressure reduction rate is lower in the transonic regime and the effectiveness of the angle of attack is greater than the subsonic and supersonic flows. Finally, a comparison with numerical result is accomplished.

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Section: Supersonic Free Streammentioning

confidence: 92%

An experimental study of binary lateral jets on a standard model in subsonic, transonic, and supersonic cross-flows

Doolabi

Sabour

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The surface oil flow visualization in their investigation provided a good understanding of the flow structure with interaction. Their work was extended to hypersonic flow 10,11) using the shock tunnel at Nagoya University. As this shock tunnel has a testing duration of about 50 milliseconds, it is difficult to perform detailed investigations including surface oil flow visualization to examine properties of the interaction.…”

Section: )mentioning

confidence: 99%

“…The same blunt body model as investigated by Kurita et al 10) is considered in the present study, which is a 10 o half-angle blunted cone with a circular sonic jet nozzle installed flush-mounted on the body surface. A schematic of the model employed in this study is shown in Fig.…”

Section: Flow Conditionsmentioning

confidence: 99%

The Role of Vortices in Side Jet/Blunt Body Interaction at Hypersonic Speed

Ibrahim

Nakamura

Kitamura

et al. 2009

Trans. JSASS Space Tech. Japan

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A numerical investigation was carried out for a blunt body with a circular sonic air jet normally injected into a hypersonic flow from the body surface, where the angle of attack was changed up to 40 • . Computed results were compared with the experimental data collected using the shock tunnel of Nagoya University. The aerodynamic interaction due to the jet creates complicated flow fields, which are rather difficult to analyze alone experimentally. The computed results show good agreement with the experimental data with regard to surface pressure distribution and schlieren visualization. It was found that at rather low angles of attack, two vortices, i.e., a separation vortex and a horseshoe vortex, are formed inside the separated boundary layer upstream of the jet. The location of these vortices corresponds to low-pressure regions in the pressure distribution. On the other hand, at a rather high angle of attack, the interaction produces a complex flow field, where vortices have little influence on the pressure distribution. Finally the jet interaction was found to enhance the jet reaction forces by about 35% -45 % on the body surface, the value of which is close to the experimental data.

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“…In the present study, two types of injector arrangements, tandem and parallel, on a hemisphere-cone model were investigated. This model was employed because interaction studies on this model with a single injection had been conducted under the same experimental condition in previous works [12,13], both experimentally and numerically. Thus, the flow field on the model had been well understood for a single injection.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on Aerodynamic Heating Induced by Dual Injections into Hypersonic Cross Flow

Taguchi

Mori

Nakamura

2017

International Journal of Aerospace Engineering

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In this study, the distribution of surface heat transfer induced by dual side-jets injected into a hypersonic flow has been visualized using a temperature sensitive paint. The experiments were performed in both tandem and parallel injector arrangements, and the spacing between the injection holes was taken as a parameter in each arrangement. As a result, the aerodynamic heating in the separated region of the boundary layer and in the horseshoe vortex was clearly visualized. In the tandem arrangements, heat transfer remarkably increased immediately upstream of the front injector. The distributions and the intensity of surface heat transfer were similar to those caused by the single injection. On the other hand, in the parallel arrangements, the extent of the separation nearly doubled, and the maximum heat flux decreased to less than half of that from the single injection. The global distribution of heat transfer varied significantly as the injector spacing was changed. When the injectors were positioned with a large spacing, the interaction between the side-jets was relatively lowered, and thus distribution, as for the single injector, was induced around each injection hole individually. In contrast, with a short spacing, the dual injection behaved as a single obstacle. The most effective reduction of maximum heat flux was achieved with an intermediate injector spacing.

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Side Jet Aerodynamic Interaction on a Blunt Body in Hypersonic Flow.

Cited by 4 publications

References 15 publications

An experimental study of binary lateral jets on a standard model in subsonic, transonic, and supersonic cross-flows

An experimental study of binary lateral jets on a standard model in subsonic, transonic, and supersonic cross-flows

The Role of Vortices in Side Jet/Blunt Body Interaction at Hypersonic Speed

Experimental Study on Aerodynamic Heating Induced by Dual Injections into Hypersonic Cross Flow

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