Development study on axisymmetric air inlet for ATREX engine

10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference

Volumn , Issue , 2001, Pages

  Kojima, Takayuki ^a   Tanatsugu, Nobuhiro ^a   Sato, Tetsuya ^a   Kanda, Masao ^a   Enomoto, Yoshinari ^b  

^a JAPAN AEROSPACE EXPLORATION AGENCY   (Japan)

^b Kawasaki Heavy Industories LTD   (Japan)

Author keywords

[No Author keywords available]

Indexed keywords

EID: 2942727461     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (8)

1. T. Sato, N. Tanatsugu, et al., Development Study on The Precooling System of ATREX Engine, IAF- 99-S.5.04,4-8 Oct 1999, Amsterdam, The Netherlands.
2. Verginia L. Sorensen. Computer Program for Calculating Flow Fields in Supersonic Inlets, NASA TND-2897, 1965
3. Bernhard H. Anderson, Design of Supersonic Inlets by a Computer Program in cooperating the Method of Characteristics, NASA TN D-4960, 1969
4. John J. Mahoney. Inlets for Supersonic Missiles, Education series, AIAA
5. nd International Symposium on Space Technology and Science, Morioka, 2000
6. J. Syberg, Design of a bleed system for a Mach 3.5 inlet, NASACR-2187, 1973
7. J.L. Koncsek, "Transonic and supersonic test of a Mach 2.65 Mixed-Compression Axisymmetric intake, NASA CR-1977, The Boeing company
8. Mitchell, "Throat stability-bypass systems to increase the stable airflow range of a mach 2.5 inlet with 60-percent internal contraction, NASA TM-X 2976, 1974