dc.contributor.author |
A. McCabe |
en_US |
dc.date.accessioned |
2014-10-21T15:56:29Z |
|
dc.date.available |
2014-10-21T15:56:29Z |
|
dc.date.issued |
1964 |
en_US |
dc.identifier.other |
ARC/R&M-3440 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/4023 |
|
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 |