A Numerical Analysis on Three-Dimensional Flow Field in a Supersonic Bump Inlet

Kim, Sang Dug; Song, Dong Joo; Lim, Seol

doi:10.2514/6.2007-689

Cited by 8 publications

(8 citation statements)

References 4 publications

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“…The past work on DSI includes experimental and computational studies on model configurations (4)(5)(6)(7)10,23) to investigate various flow features. The application of top-mounted DSI on an unmanned ariel vehicle has been studied by Tan et al (20,21) who reported favourable generally consistent with the experimental data (14) (to be discussed later in this paper), therefore further trials with different turbulence models was not done.…”

Section: Introductionmentioning

confidence: 99%

Flow field and performance analysis of an integrated diverterless supersonic inlet

Masud

2011

Aeronaut. j.

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Section: Introductionmentioning

confidence: 99%

Flow field and performance analysis of an integrated diverterless supersonic inlet

Masud

2011

Aeronaut. j.

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“…Their detailed study included the flow field surrounding the bump exclusively (Tillotson et al, 2009). Kim et al (2007) numerically studied a three dimensional bumped type inlet which was a modification of a conventional ramped type one previously used by Loth et al (2004). Please note that the present authors simulated this inlet threedimensionally and investigated its shock boundary layer interaction (Askari and Soltani, 2018).…”

Section: Aipmentioning

confidence: 99%

“…Kim et al further, studied the performance of supersonic inlets incorporating various three-dimensional bumps numerically (Kim and Song, 2008). Their simulations included effects of the geometrical features of the bump to control the interaction of shock wave and boundary layer at a free stream Mach number of ∞ =2 (Kim, Song, and Lim, 2007;Kim and Song, 2008;Kim, 2009). Masud et al (2011), numerically investigated performance of a DSI integrated with an aircraft typed body at low angles of attack, for both subsonic and supersonic Mach numbers of 0.8 and 1.65 respectively.…”

Section: Aipmentioning

confidence: 99%

Angle of Attack Investigations on the Performance of a Diverterless Supersonic Inlet

Askari

Soltani

Mostoufi

et al. 2019

JAFM

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An extensive experimental investigation to study the effects of angle of attack (AOA) on the performance of a body-integrated supersonic inlet has been carried out. The present inlet, known as Diverterless Supersonic Inlet (DSI), is utilized with a three-dimensional bump to provide both supersonic flow compression and boundary layer diversion. Experiments were conducted at the presence of a typical fore-body including an elliptical nose to further contemplate the effects of fore-body geometry on the approaching flow. All tests were conducted at a constant free stream Mach number, ∞ = 1.65 zero degrees angle of sideslip (AOS), and at various angles of attack (AOA) ranging from-2 to 6 degrees. The results showed that the present DSI had acceptable performance characteristics for all ranges of AOA tested. It should be noted that the present DSI does not have any moving, adjustable or auxiliary mechanisms as such systems or mechanism are used to improve the performance of an inlet.

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“…The bump is located on a highly curved waverider surface. Previous research and practical bump designs have considered a flat surfaces for inlet-bump installation 5,6 so that the flow pattern and the boundary layer diverting ability of new bump geometry on a highly curved surface needs to be measured. For this purpose, two basic bump structures are designed and analyzed numerically.…”

Section: Stream-traced Bump and Curved Intersecting Surfacementioning

confidence: 99%

“…Using the effect of the pressure gradient on the low energy boundary layer of a compressible flow, this wave-derived surface diverts the boundary layer into its sides. [4][5][6] The bump concept is successfully used on supersonic fighter jets such as the F-35 and J-17, but there are less data about hypersonic usage and designs.…”

Section: Introductionmentioning

confidence: 99%

Design of hypersonic forebody with submerged bump

Saheby

Huang

Hays

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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A double shock waverider forebody configuration, with curved surfaces and known pressure fields and shock arrays, is constructed by a stream-tracing approach. The compression surface consists of a wedge and conical shocks. The conical shock results from a modified wave-derived bump surface that diverts the boundary layer before the inlet entrance. The design is fully computational fluid dynamics based and emphasis is placed on the compact design with boundary layer diverting ability. Controlling or diverting the thick boundary layer safely is a difficult challenge in hypersonic flight vehicle design especially when the inlets are highly integrated with the fuselage. Numerical simulations show that the new combination can divert a significant fraction of boundary layer before the inlet and maintains a good compression ratio for propulsion efficiency at Mach 5.0. Effects of forebody aerodynamics on the integrated inlet and comparisons with other systems are described in this paper.

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A Numerical Analysis on Three-Dimensional Flow Field in a Supersonic Bump Inlet

Cited by 8 publications

References 4 publications

Flow field and performance analysis of an integrated diverterless supersonic inlet

Flow field and performance analysis of an integrated diverterless supersonic inlet

Angle of Attack Investigations on the Performance of a Diverterless Supersonic Inlet

Design of hypersonic forebody with submerged bump

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