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 conferencePaperpeer-review

13 Citations (Scopus)


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 languageEnglish
Number of pages9
Publication statusPublished - 2004 Jul 1
Externally publishedYes
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: 2004 Jan 52004 Jan 8


Conference42nd AIAA Aerospace Sciences Meeting and Exhibit
Country/TerritoryUnited States
CityReno, NV

ASJC Scopus subject areas

  • Engineering(all)


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