Title: Three-dimensional flow over a conical afterbody containing a centered propulsive jet - A numerical simulation
Abstract: The supersonic flow field over a body of revolution incident to the free stream is simulated numerically on a large, array processor (the CDC CYBER 205). The configuration is composed of a cone-cylinder forebody followed by a conical afterbody from which emanates a centered, supersonic propulsive jet. The free-stream Mach number is 2, the jet-exist Mach number is 2.5, and the jet-to-free-stream static pressure ratio is 3. Both the external flow and the exhaust are ideal air at a common total temperature.
Publication Year: 1984
Publication Date: 1984-03-01
Language: en
Type: article
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Cited By Count: 11
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