Design of a supersonic nozzle

Show simple item record A. McCabe en_US 2014-10-21T15:56:29Z 2014-10-21T15:56:29Z 1964 en_US
dc.identifier.other ARC/R&M-3440 en_US
dc.description.abstract This paper presents a method of design of a supersonic nozzle which incorporates recent developments in compressible flow theory. Continuous curvature of the contour is ensured by defining a continuous gradient of Prandtl-Meyer angle along the nozzle axis. The flow in the throat was calculated from results given by Hall (1962). A matching technique was used to determine a triplet of values for the throat radius of curvature, the flow deflection at the inflection point and the Prandtl-Meyer angle at the point on the nozzle axis where the left-running characteristic through the inflection point intersects the nozzle axis. The majority of the new work is to be found in the Appendices. Appendix B presents a method of determining the co-ordinates along a particular characteristic by inverting the results given by Hall (1962). Appendix C reviews the accuracy of the method of characteristics and, Appendix D suggests a method by which it may be possible to increase the accuracy Without resorting to calculations made at very small step sizes. en_US
dc.relation.ispartofseries Aeronautical Research Council Reports & Memoranda en_US
dc.title Design of a supersonic nozzle en_US

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