Description of compressible gas flow in throat region of rocket nozzles must be known to optimize wall contours and to predict performance; existence of subsonic and supersonic flow in close proximity does not permit use of conventional analytical techniques to obtain mathematical description of flow; analysis presented can treat annular flow passages that are either parallel to nozzle axis or inclined to it at some arbitrary angle; solution is not limited to nozzles with moderate wall radii of curvature; it is expected that solution will provide accurate starting conditions for method of characteristics to compute flowfield in supersonic region.
Transonic flow in unconventional nozzles
AIAA J
AIAA Journal ; 6 , n 5
1968
5 pages
Article (Journal)
English
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Transonic flow in unconventional nozzles.
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