Experimental study of multi-row disk inlets for hypersonic air breathing propulsion

Hiroaki Kobayashi; Nobuhiro Tanatsugu; Tetsuya Sato; Yusuke Maru; Takayuki Kojima

Experimental study of multi-row disk inlets for hypersonic air breathing propulsion

Hiroaki Kobayashi^*, Nobuhiro Tanatsugu, Tetsuya Sato, Yusuke Maru, Takayuki Kojima

^*Corresponding author for this work

Research output: Contribution to conference › Paper › peer-review

13 Citations (Scopus)

Abstract

This paper proposes a new supersonic inlet, which is called Multi-Row Disk (MRD) inlet The MRD inlet has a centerbody being composed of a tip cone and following disks. Because centerbody geometry is variable by changing space between disks, air compression ratio and mass capture ratio of this inlet can be controlled independently of each other. However, conical cavity flow formed between disks may affect the boundary layer profile negatively resulting in the deteriorated performance of inlets. We made a basic research on conical cavity flow and validation tests of the MRD inlet in 2002 and 2003. There was significant improvement in the off-design point performance of the MRD inlet relative to general axisymmetnc inlets.

Original language	English
Pages	9652-9660
Number of pages	9
Publication status	Published - 2004 Jul 1
Externally published	Yes
Event	42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: 2004 Jan 5 → 2004 Jan 8

Conference

Conference	42nd AIAA Aerospace Sciences Meeting and Exhibit
Country/Territory	United States
City	Reno, NV
Period	04/1/5 → 04/1/8

ASJC Scopus subject areas

Engineering(all)

Cite this

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title = "Experimental study of multi-row disk inlets for hypersonic air breathing propulsion",

abstract = "This paper proposes a new supersonic inlet, which is called Multi-Row Disk (MRD) inlet The MRD inlet has a centerbody being composed of a tip cone and following disks. Because centerbody geometry is variable by changing space between disks, air compression ratio and mass capture ratio of this inlet can be controlled independently of each other. However, conical cavity flow formed between disks may affect the boundary layer profile negatively resulting in the deteriorated performance of inlets. We made a basic research on conical cavity flow and validation tests of the MRD inlet in 2002 and 2003. There was significant improvement in the off-design point performance of the MRD inlet relative to general axisymmetnc inlets.",

author = "Hiroaki Kobayashi and Nobuhiro Tanatsugu and Tetsuya Sato and Yusuke Maru and Takayuki Kojima",

year = "2004",

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T1 - Experimental study of multi-row disk inlets for hypersonic air breathing propulsion

AU - Kobayashi, Hiroaki

AU - Tanatsugu, Nobuhiro

AU - Sato, Tetsuya

AU - Maru, Yusuke

AU - Kojima, Takayuki

PY - 2004/7/1

Y1 - 2004/7/1

N2 - This paper proposes a new supersonic inlet, which is called Multi-Row Disk (MRD) inlet The MRD inlet has a centerbody being composed of a tip cone and following disks. Because centerbody geometry is variable by changing space between disks, air compression ratio and mass capture ratio of this inlet can be controlled independently of each other. However, conical cavity flow formed between disks may affect the boundary layer profile negatively resulting in the deteriorated performance of inlets. We made a basic research on conical cavity flow and validation tests of the MRD inlet in 2002 and 2003. There was significant improvement in the off-design point performance of the MRD inlet relative to general axisymmetnc inlets.

AB - This paper proposes a new supersonic inlet, which is called Multi-Row Disk (MRD) inlet The MRD inlet has a centerbody being composed of a tip cone and following disks. Because centerbody geometry is variable by changing space between disks, air compression ratio and mass capture ratio of this inlet can be controlled independently of each other. However, conical cavity flow formed between disks may affect the boundary layer profile negatively resulting in the deteriorated performance of inlets. We made a basic research on conical cavity flow and validation tests of the MRD inlet in 2002 and 2003. There was significant improvement in the off-design point performance of the MRD inlet relative to general axisymmetnc inlets.

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M3 - Paper

AN - SCOPUS:2942709841

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T2 - 42nd AIAA Aerospace Sciences Meeting and Exhibit

Y2 - 5 January 2004 through 8 January 2004

ER -

Experimental study of multi-row disk inlets for hypersonic air breathing propulsion

Abstract

Conference

ASJC Scopus subject areas

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