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Performance Study of Supersonic Nozzle with Asymmetric Entrance Shape  

Lee Ji-Hyung (국방과학연구소)
Kim Joug-Keun (국방과학연구소)
Lee Do-Hyung (국방과학연구소)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.10, no.2, 2006 , pp. 46-52 More about this Journal
Abstract
Techniques used for thrust vector control in rocket motors are mainly classified nozzles installed mechanical interference on the expansive region of nozzle(such as jet tabs and jet vanes) and movable nozzles(such as ball&socket and flexible seal). Using the numerical analysis and cold-flow test, this paper evaluates the performance of supersonic nozzle with asymmetric entrance shape when the test nozzle, especially ball&socket, is tilted. Numerical result shows that the effect of the asymmetric entrance shape on the flow field is suddenly diminished at the nozzle throat and downstream is mostly free from the effect of asymmetric entrance shape. Although the calculated thrust and lateral force are less than those of cold-flow test, two results show a fairly good agreement. But the cold-flow test results indicate the effective angles calculated from measured forces are not agreement with the geometric angles.
Keywords
Thrust Control; Ball & Socket Nozzle; Asymmetric Entrance Shape; Nozzle Performance; Flow Separation;
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  • Reference
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