Supersonic wind-tunnel : nozzle design and control system analysis

 

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dc.contributor.advisor Gryzagoridis, Jasson en_ZA
dc.contributor.author Cox, Riordan Howard Tesling en_ZA
dc.date.accessioned 2016-03-14T07:16:58Z
dc.date.available 2016-03-14T07:16:58Z
dc.date.issued 1973 en_ZA
dc.identifier.citation Cox, R. 1973. Supersonic wind-tunnel : nozzle design and control system analysis. University of Cape Town. en_ZA
dc.identifier.uri http://hdl.handle.net/11427/17711
dc.description.abstract Symmetrical two-dimensional nozzles were designed for the supersonic wind-tunnel, in the Department of Mechanical Engineering, using both analytical and semigraphical methods obtained from the theory of Characteristics. These nozzles, designed for an optimum running time of 30 seconds, at a Mach number of 2,35. Boundary layer growth was considered by displacing the nozzle contours outwards by the equivalent displacement thickness, while keeping the vertical tunnel side walls parallel. The five pitot probe calibration results, taken through the central vertical plane in the tunnel test-section, showed Mach number standard deviations about the mean of 0,638% and 1,004% for the analytical and semi-graphical design respectively. These results compare ·very favourably with those of other wind- tunnels. Without pressure recovery the critical flow pressure ratio through the tunnel for Mach 2,35 nozzles, is 2,53. Therefore it may be shown that the subsonic diffuser, and the silencer incorporated into it, is about 75% efficient. The analysis and modification to the existing settling chamber control valve yielded improvements in performance. 1. The maximum fluctuation in settling chamber pressure was kept to within 5,5% for most operating conditions. 2. Critical valve response was achieved by applying a suitable bypass orifice to the damping cylinder - The valve settled down within one second after flow had been initiated. A proposed variable symmetrical nozzle was examined for the feasibility of its application to the existing supersonic wind-tunnel. en_ZA
dc.language.iso eng en_ZA
dc.subject.other Mechanical Engineering en_ZA
dc.title Supersonic wind-tunnel : nozzle design and control system analysis en_ZA
dc.type Master Thesis
uct.type.publication Research en_ZA
uct.type.resource Thesis en_ZA
dc.publisher.institution University of Cape Town
dc.publisher.faculty Faculty of Engineering and the Built Environment
dc.publisher.department Department of Mechanical Engineering en_ZA
dc.type.qualificationlevel Masters
dc.type.qualificationname MSc (Eng) en_ZA
uct.type.filetype Text
uct.type.filetype Image
dc.identifier.apacitation Cox, R. H. T. (1973). <i>Supersonic wind-tunnel : nozzle design and control system analysis</i>. (Thesis). University of Cape Town ,Faculty of Engineering & the Built Environment ,Department of Mechanical Engineering. Retrieved from http://hdl.handle.net/11427/17711 en_ZA
dc.identifier.chicagocitation Cox, Riordan Howard Tesling. <i>"Supersonic wind-tunnel : nozzle design and control system analysis."</i> Thesis., University of Cape Town ,Faculty of Engineering & the Built Environment ,Department of Mechanical Engineering, 1973. http://hdl.handle.net/11427/17711 en_ZA
dc.identifier.vancouvercitation Cox RHT. Supersonic wind-tunnel : nozzle design and control system analysis. [Thesis]. University of Cape Town ,Faculty of Engineering & the Built Environment ,Department of Mechanical Engineering, 1973 [cited yyyy month dd]. Available from: http://hdl.handle.net/11427/17711 en_ZA
dc.identifier.ris TY - Thesis / Dissertation AU - Cox, Riordan Howard Tesling AB - Symmetrical two-dimensional nozzles were designed for the supersonic wind-tunnel, in the Department of Mechanical Engineering, using both analytical and semigraphical methods obtained from the theory of Characteristics. These nozzles, designed for an optimum running time of 30 seconds, at a Mach number of 2,35. Boundary layer growth was considered by displacing the nozzle contours outwards by the equivalent displacement thickness, while keeping the vertical tunnel side walls parallel. The five pitot probe calibration results, taken through the central vertical plane in the tunnel test-section, showed Mach number standard deviations about the mean of 0,638% and 1,004% for the analytical and semi-graphical design respectively. These results compare ·very favourably with those of other wind- tunnels. Without pressure recovery the critical flow pressure ratio through the tunnel for Mach 2,35 nozzles, is 2,53. Therefore it may be shown that the subsonic diffuser, and the silencer incorporated into it, is about 75% efficient. The analysis and modification to the existing settling chamber control valve yielded improvements in performance. 1. The maximum fluctuation in settling chamber pressure was kept to within 5,5% for most operating conditions. 2. Critical valve response was achieved by applying a suitable bypass orifice to the damping cylinder - The valve settled down within one second after flow had been initiated. A proposed variable symmetrical nozzle was examined for the feasibility of its application to the existing supersonic wind-tunnel. DA - 1973 DB - OpenUCT DP - University of Cape Town LK - https://open.uct.ac.za PB - University of Cape Town PY - 1973 T1 - Supersonic wind-tunnel : nozzle design and control system analysis TI - Supersonic wind-tunnel : nozzle design and control system analysis UR - http://hdl.handle.net/11427/17711 ER - en_ZA


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