Development study on axisymmetric air inlet for ATREX engine

Takayuki Kojima, Nobuhiro Tanatsugu, Tetsuya Satou, Masao Kanda, Yoshinari Enomoto

Research output: Chapter in Book/Report/Conference proceedingConference contribution

15 Citations (Scopus)

Abstract

A development study of variable geometry axisymmetric inlet has been done at ISAS since 1993. Total pressure recovery and mass capture ratio of the inlets are obtained by the wind tunnel tests at ISAS supersonic wind tunnel and NASA GRC 1-by 1-foot supersonic wind tunnel. In Feb 2000, a control test of an inlet is conducted at ONERA S3MA supersonic wind tunnel to accomplish an automatic operation of the inlet. As a result, we succeeded in controlling the inlet automatically and about 90% of the maximum inlet performances are achieved without manual operation. The configuration of the supersonic and subsonic diffuser is modified to increase the mass capture in the subsonic flight without the increase of the total pressure loss in the supersonic flight, and new type of inlet configuration is designed (Type-M). Although, type-M inlet can make 75% of total pressure recovery at Mach 3.5, it is necessary to improve the bleed system of the spike surface. A flyable inlet model whose cowl diameter is 740mm is now on the drawing board.

Original languageEnglish
Title of host publication10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference
Publication statusPublished - 2001
Externally publishedYes
Event10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001 - Kyoto
Duration: 2001 Apr 242001 Apr 27

Other

Other10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001
CityKyoto
Period01/4/2401/4/27

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ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Control and Systems Engineering

Cite this

Kojima, T., Tanatsugu, N., Satou, T., Kanda, M., & Enomoto, Y. (2001). Development study on axisymmetric air inlet for ATREX engine. In 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference