Comparative flow path analysis and design assessment of an axisymmetric hydrogen fueled scramjet flight test engine at a mach number of 6. 5

Space Plane and Hypersonic Systems and Technology Conference

Volumn , Issue , 1996, Pages

  McClinton, C ^a,d   Roudakov, A ^b,c   Semenov, V ^b,c   Kopehenov, V ^b,c  

^a NASA LANGLEY RESEARCH CENTER   (United States)

^b CENTRAL INSTITUTE OF AVIATION MOTORS   (Russian Federation)

^c Aerospace Propulsion Department   (Russian Federation)

^d Numerical Applications Office   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; COMBUSTION; COMBUSTORS; ENGINES; MACH NUMBER; MOLLUSCS; NASA; REGRESSION ANALYSIS; SHELLFISH; SPACECRAFT; UNMANNED VEHICLES;

COMBUSTOR COOLING; DESIGN ASSESSMENTS; FLIGHT TEST ENGINE; OPERATING POINTS; SHOCK-SHOCK INTERACTIONS; SUPERSONIC COMBUSTION RAMJET (SCRAMJET); THERMAL ASSESSMENT; THERMAL EVALUATIONS;

SUPERSONIC AIRCRAFT;

EID: 84983189864     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (12)

1. A. Roudakov, J. Schickman, V. Semenov, P. Novelli, O. Fourt: Flight testing an axisymmetrical scramjet- Russian recent advances. 44th Congress of the IAF. Oct. 16-22, 1993. Graz, Austria.
2. A. Roudakov, V. Semenov and V. Kopehenov and J. Hick; Future Flight Test Plans of an Axisymmetric Hydrogen-Fueled Scramjet Engine on the Hypersonic Flying Laboratory. Presented at the 7th International Spaceplanes and Hypersonic Conference. AIAA Paper 96-4572, Nov. 1996
3. CIAM Staff; Characteristic features of the design and manufacture procedure of axisymmetrical scramjet for flight tests on HFTB "Kholod". CIAM Technical Report. NASW4969, 1 Aug. 1996.
4. CIAM Technical Report, Feasibility determination of conducting hydrogen scramjet flight test with flight Mach number Mf=7 on hypersonic flying laboratory with rocket acceleration system (GASL contract N 4799), 23 Oct. 1993.
5. CIAM TR, Experimental scramjet for flight tests on HFL "KHOLOD" at flight Mach Mp6. 5. Preliminary choice and justification of engine configuration, design description. (NASA contract NASW- 4969), 17 Nov. 1994.
6. McGrory, W. D., Huebner, L. D., Slack, D. C, and Walters, R. W.: Development and application of GASP 2. 0. AIAA Paper 92-5067, Dec. 1992.
7. Kamath, P., Mao, M.., and McClinton, C.: Scramjet combustor analysis with the SHIP 3-D PNS Code., AIAA paper 91-5090, Dec. 1991
8. Cubbage, J. M.: Effect of nose bluntness and controlled roughness on the flow on two hypersonic inlet center bodies without cowling at mach 5. 98. NASA TN D-2900, July, 1965.
9. Rogers, R. C.: Mixing of hydrogen injected from multiple injectors normal to a supersonic airstream. NASA TN- D-6476, Sept. 1971.
10. Huber, P. W., Schexnayder, C. J. and McClinton, C. R.: Criteria for self-ignition of supersonic hydrogen-air mixtures. NASA TP-1457 Aug. 1979.
11. McClinton, C. R.: Autoignition of Hydrogen injected transverse to a supersonic airstream. AIAA 79-1239, June 1979.
12. H. Inouye; Niobium in High temperature applications. Proceedings of the International Symposium, Niobium. The Metal. lurgical Society of AIME, San Francisco, CA., Nov. 8-11. 1981.