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Study of the Two-Dimensional Flow Through a Converging-Diverging NozzleA study of a flow through a straight converging-diverging nozzle of simple design has been made preliminary to studies of other supersonic flows. The diverging part of the nozzle was designed by the Prandtl-Busemann method to give a uniform pressure at its exit of 0.298 times the initial total head, that is, to give a Mach number of 1.436. Schlieren photographs of the flow and pressure-distribution measurements along the diverging part of the nozzle were made. A comparison of the theory with these measurements is presented.
Document ID
20160011535
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Kantrowitz, Arthur (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Street, Robert E. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Erwin, John R. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 27, 2016
Publication Date
April 1, 1943
Subject Category
Fluid Mechanics And Thermodynamics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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