Title: Internal pressure distributions for a two-dimensional thrust-reversing nozzle operating at a free-stream Mach number of zero
Abstract: An investigation was conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to measure static pressure distributions inside a nonaxisymmetric thrust reversing nozzle. The tests were made at nozzle total pressures ranging from ambient to about eight times ambient pressure at a free stream Mach number of zero. Tabulated pressure data are presented.
Publication Year: 1983
Publication Date: 1983-12-01
Language: en
Type: article
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Cited By Count: 3
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