An analytical and experimental study of a short S-shaped subsonic diffuser of a supersonic inlet

Neumann, H. E.; Povinelli, Louis A.; Coltrin, R. E.

doi:10.2514/6.1980-386

Cited by 7 publications

(4 citation statements)

References 1 publication

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“…Oetails of the generator design are given in Ref . 1. A comparison of the total pressure profile at the mid-diffuser with and without vortex generators is given in Fig.…”

Section: Resultsmentioning

confidence: 99%

“…The design of the vortex generators is given in Ref . 1. The installation of the vortex generators in the inlet is shown in Fig.…”

Section: Inlet Detailsmentioning

confidence: 99%

“…Geometric details of the inlet configuration can be obtained from Ref. 1. The inlet was coupled to a coldpipe-choked plug assembly which maintained choked flow conditions a short distance downstream of the compressor face instrumentation .…”

Section: Inlet Detailsmentioning

confidence: 99%

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Dynamic distortion in a short s-shaped subsonic diffuser with flow separation

Stumpf

Neumann

Giamati

1983

19th Joint Propulsion Conference

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An experimental investigation of the time varying distortion at the diffuser exit of a subscale HiMAT fore body and inlet was conducted at Mach 0.9 in the Lewis 8 by 6 Foot Supersonic Wind Tunnel. A transitory separation was detected within the subsonic diffuser . Vortex generators were installed to eliminate the flow separation . This paper will present results from a study of the instantaneous pressure variations at the diffuser exit . The time unsteady total pressures at the diffuser exit are computer interpolated and presented in the form of a movie showing the transitory separation. Limited data showing the instantaneous distortion levels is also presented.Nomenclature

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“…Oetails of the generator design are given in Ref . 1. A comparison of the total pressure profile at the mid-diffuser with and without vortex generators is given in Fig.…”

Section: Resultsmentioning

confidence: 99%

“…The design of the vortex generators is given in Ref . 1. The installation of the vortex generators in the inlet is shown in Fig.…”

Section: Inlet Detailsmentioning

confidence: 99%

See 1 more Smart Citation

Dynamic distortion in a short s-shaped subsonic diffuser with flow separation

Stumpf

Neumann

Giamati

1983

19th Joint Propulsion Conference

Self Cite

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“…Late in the forties, the generators by Taylor (1) was used to delay the separation of the flow on the wing surface to increase the critical Mach number and to prevent the boundary layer separation in the diffuser for increasing the diffuser efficiency. At present they are still used as the main way to prevent and reduce the separation and to improve the flow field nonuniformity at the diffuser exit (2,3,4).…”

Section: Introductionmentioning

confidence: 99%

Application of Vortex Generators in Flow Control of the Inlet

Chen¹,

Fang²

1985

Volume 1: Aircraft Engine; Turbomachinery

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This paper introduces the features of using co-rotating vortex generators for controlling boundary layer and flow field in the inlet without flow separation. The principles of the arrangements of the blades and selection of constructional parameters of the generators that are applied to create the transverse flow between the high and low pressure regions and to reduce the secondary flow losses are analysed. The experimental results show that when the appropriate parameters of the co-rotating vortex generators are chosen for the inlet subsonic diffuser with apparent high and low pressure regions, not only the nonuniformity of the flow field is greatly improved but also the dynamic performance of the flow at exit is slightly improved.

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