Numerical Study of Hypervelocity Flows Through a Scramjet Combustor-Reference-Cited by-同舟云学术

Numerical Study of Hypervelocity Flows Through a Scramjet Combustor

Published:1997-01 Issue:1 Volume:13 Page:131-141
ISSN:0748-4658
Container-title:Journal of Propulsion and Power
language:en
Short-container-title:Journal of Propulsion and Power

Author:

Krishnamurthy R.¹,Rogers R. C.²,Tiwari S. N.³

Affiliation:

1. North Carolina A&T State University, Greensboro, North Carolina 27411

2. NASA Langley Research Center, Hampton, Virginia 23681

3. Old Dominion University, Norfolk, Virginia 23529

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/2.5138

Reference18 articles.

1. Performance data of the new free-piston shock tunnel at GALCIT

2. Hypervelocity real gas capabilities of GASL's expansion tube (HYPULSE) facility

3. The G-range impulse facility - A high-performance free-piston shock tunnel

4. 5Belanger, J. “Studies of Mixing and Combustion in Hypervelocity Flows with Hot Hydrogen Injection,” Ph.D. Dissertation, California Inst. of Technology, Pasadena,CA, April 1993.

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