An investigation, both theoretical and experimental in nature, has
been undertaken to develop a simple method for the design of
supersonic nozzles and, indeed, inlets of quite complex shapes from
known or calculated axisymmetric flowfields.
1he axisymmetric flowfield is determined using a computer program
based on the method of characteristics. Streamlines are calculated by
direct integration of the axisymmetric stream function.
7he desired shape is chosen at the exit of the computed
axisymmetric nozzle having the desired length and Mach number. Its
describing points are then traced along the corresponding streamlines
back to the throat. Streamsheets formed by these streamlines define
the new shape.
Following this approach, two three-dimensional nozzles were
designed : one of elliptical cross-section and a two-dimensional
wedge. Flows within the two configurations were further simulated
using a general purpose three-dimensional CFD code, "PHOENICS", while
the elliptical nozzle was subsequently manufactured and submitted to
experimental tests.
Results from the experimental tests and three-dimensional
numerical simulation, as well as predictions of the performance of
the nonaxisymmetric nozzles and their axisymmetric counterparts were
obtained and compared.
Good agreement was achieved between the several components of the
study demonstrating that it is possible, using this relatively simple
method, to design satisfactory three-dimensional nozzles
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