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Hypersonic flow, Hypersonic shock tubesEdition | Availability |
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An investigation of hypersonic shock tunnel testing at an equilibrium interface condition of 4,100K: theory and experiment
1991, American Institute of Aeronautics and Astronautics
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Book Details
Edition Notes
Includes bibliographical references: p. 11-12.
Source: AIAA 22nd Fluid Dynamics, Plasma Dynamics & Lasers Conference, June 24-26, 1991/Honolulu, Hawaii
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